Modular array wind energy nozzles with truncated catenoidal curvature to facilitate air flow

ABSTRACT

In embodiments of the present invention improved capabilities are described for a wind energy conversion system including a plurality of wind energy conversion modules integrated into a superstructure for the conversion of wind energy to electrical energy, each one of the plurality of wind energy conversion modules including a nozzle comprising: an intake having an intake length; a throat coupled in fluid communication with a wind power generating turbine, wherein the throat is downstream of the intake; a diffuser comprising a housing and having a length, the diffuser downstream from the throat, wherein a diameter of the diffuser is greater than a diameter of the throat; and a vortex-forming aerodynamic feature on at least one of the intake, the throat, the turbine, and the diffuser, wherein the aerodynamic feature acts to increase throughput through the nozzle.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No.13/448,802 filed Apr. 17, 2012, which is a continuation of U.S. patentapplication Ser. No. 13/292,786 filed Nov. 9, 2011 (now U.S. Pat. No.8,178,990 issued May 15, 2012), which is a continuation of U.S. patentapplication Ser. No 12/861,263 filed Aug. 23, 2010 (now U.S. Pat. No.8,089,173 issued Jan. 3, 2012), which is a continuation of U.S. patentapplication Ser. No. 12/332,313 filed Dec. 10, 2008 (now U.S. Pat. No.7,804,186 issued Sep. 28, 2010), which claims the benefit of U.S.Provisional App. No. U.S. 61/012,759, filed Dec. 10, 2007, each of whichis hereby incorporated by reference in its entirety.

FIELD OF INVENTION

The present invention is related to energy conversion, and in certainpreferred embodiments to the energy conversion from a fluid flow, suchas wind, to another type of energy, such as electrical energy.

BACKGROUND

The conversion of energy from a fluid flow, such as from the wind, toelectrical energy has been typically implemented in the past with largesingular horizontal axis turbines. The energy conversion efficiency forsuch a configuration may be limited. As alternate energy sources such aswind energy are increasingly utilized to counter the rising energy costsof fossil fuels, it becomes more vital that energy efficienciesassociated with these alternate energy sources be maximized. A needexists for improved methods and systems for converting energy from afluid flow to electrical energy.

SUMMARY

Improved capabilities are described for the efficiency with which fluidenergy is converted into another form of energy, such as electricalenergy. In embodiment, an array of fluid energy conversion modules iscontained in a scalable modular networked superstructure. In certainpreferred embodiments, a plurality of turbines, such as for instancewind turbines, may be disposed in an array in a suitable arrangement inproximity to each other and provided with geometry suitable for tightpacking in an array with other parameters optimized to extract energyfrom the fluid flow. In addition, the turbines may be a more effectiveadaptation of a turbine, or an array of turbines, to varying conditions,including fluid conditions that may differ among different turbines inan array, or among different turbines in a set of arrays.

These and other systems, methods, objects, features, and advantages ofthe present invention will be apparent to those skilled in the art fromthe following detailed description of the preferred embodiment and thedrawings. All documents mentioned herein are hereby incorporated intheir entirety by reference.

BRIEF DESCRIPTION OF THE FIGURES

The invention and the following detailed description of certainembodiments thereof may be understood by reference to the followingfigures:

FIG. 1 depicts a kinetic access facility.

FIG. 2 depicts a kinetic access facility array.

FIG. 3 depicts a square polygon expansion exit, module, and array.

FIG. 4 depicts a complex topography connector and members.

FIGS. 5A and 5B depict examples of structural members of variabledensity and profile.

FIGS. 6A and 6B depict linear scalloping on a surface and in profile.

FIG. 7 depicts an 85 m×51 m uniform array compared with the same area ofa 75 m horizontal axis wind turbine.

FIG. 8 depicts a 100 m×44 m uniform array compared with the same area ofa 75 m horizontal axis wind turbine.

FIGS. 9A and 9B depict a series of arrays side and front elevations.

FIG. 10 depicts non-uniform array with orientation tails.

FIG. 11 depicts an array with three integrated generators.

FIG. 12 depicts an integrated generator-module example.

FIG. 13 depicts an array with storage.

FIG. 14 depicts a module in a triangular superstructure.

FIG. 15 depicts components of a nozzle.

FIG. 16 depicts two nozzles in a serial arrangement.

FIG. 17 depicts a side elevation of a hexagonal nozzle.

FIG. 18 depicts a nozzle with a circular throat and polygonal exit.

FIG. 19 depicts two nested nozzles.

FIG. 20 depicts a superstructure connector.

FIG. 21 depicts a horizontal axis wind turbine generator arrangement.

FIG. 22 depicts a superstructure and module arrangement for hexagonalmodules.

FIG. 23 depicts a space frame for a square array.

FIG. 24 depicts examples of nozzle polygon entrances.

FIG. 25 depicts an example of power transfer in a square array.

FIG. 26 depicts a diagram of an initial intake momentum vector.

FIG. 27 depicts a nozzle with truncation intake and exit.

FIG. 28 depicts a nozzle with truncated intake and 1/r-0 interpolatedcurvature.

FIG. 29 depicts an arc section diagram for inlet geometry.

FIG. 30 depicts a multi-blade configuration

FIG. 31 depicts a 3-blade rotor efficiency plot.

FIG. 32 depicts a plot of annual velocity distribution.

FIG. 33 depicts an annual distribution power output by linear velocity.

FIG. 34 depicts annual distribution with heavier loading to shift.

FIG. 35 depicts 12 blades in an open position, where velocity isapproximately in the range of 1-3 m/s.

FIG. 36 depicts 6 blades in an open position, where velocity isapproximately in the range of 3-6 m/s.

FIG. 37 depicts 3 blades in a closed position, where velocity isapproximately 6+m/s.

FIG. 38 depicts a sample of open and closed profiles.

FIG. 39 depicts a rotor consisting of a rotatable body with a centralmass reservoir.

FIG. 40 depicts an initial position for a weighted structure.

FIG. 41 depicts a weighted structure in a subsequent position.

FIG. 42 depicts a 3 blade structure in motion.

FIG. 43 depicts a 3 blade structure with mass control channel andcentral mass reservoir.

DETAILED DESCRIPTION

The present invention may include an n×m modular array having a numberof energy producing modules (in certain preferred embodiments, windturbines) arranged in the array and oriented with respect to a fluidflow, with a plurality of modular energy conversion units optimallyplaced in a given array configuration to maximize energy output.

In embodiments, the fluid flow toward which the array is oriented may bepreferably a natural or artificial generated differential flow, such aswind, solar chimney, a differential tunnel flow, and the like in thenatural case, or in the artificial case, but may also be a “wake” flowor its inverse that is generated by a motive force, such a tide,rotation, fluid, gas displacement, and the like. FIG. 1 depicts anembodiment of the invention, showing components of four representativemodules 110 in an array 124 with superstructure and electricalinfrastructure, including a nozzle facility 104 (which in turn may havestructural characteristics and an orientation facility), a kineticenergy access facility 108 (which may include a rotor, such as withblades and a hub), a drive facility 112 (such as a transmission drivefacility), a generator 122, structure 102, orientation facility 114,blades 118, hub 120, and the like. In embodiments, the array 124 ofmodules 110 may be associated with an integrated or non-integratedsuperstructure and electrical infrastructure that may interface withenergy handling facilities 130 and energy storage facilities 132. Itshould be understood that any number of modules 110 might be provided inan array 124, with optimal arrays 124 possibly including far more thanfour modules 110.

As depicted in FIG. 1, a bearing 128, such as a ball roller bearing, andthe like, or such as a material property bearing, such as a Teflonbearing or the like, or a fluid bearing, magnetic bearing, monolithicbearing such as a cone/ball bearing, and the like, or some combinationbearing having all or a portion of the properties of these bearings maybe used to support an array of modules, such as to allow the array torotate about a vertical axis, allowing the array to be oriented (or toself-orient, as described below in certain preferred embodiments) withrespect to a direction of fluid flow. In the case where a magneticbearing or similar bearing structure is used, the bearing structure maygenerate additional energy either for immediate use or for temporarystorage. The drive facility and generator may be associated with anelectrical infrastructure including a conducting medium such asconductive metals, conductive fluids, and the like, such asmagnetorhetological fluids, ferrofluid, superconductors, and the like,or a conducting gas, which may be integrated or associated with thesuperstructure of the array, so that energy from the modules may bepassed to an external energy handling facility, and optionally to alocal or global energy storage facility, such as a flywheel, compressedair, gravitational storage (pumping fluid, gas or solids up a heightdifferential), battery, plurality of batteries, and the like to anenergy conversion facility, such as an electrolysis hydrogen and oxygenproduction facility, or some combination of transport, end-use, storage,facilities, and the like. In embodiments, the magnetic propertiesassociated with electrical distribution or transmission system may beutilized to help orient the array, such as in generator rotor (e.g. usethe magnetic properties of the electrical flow to excite a stator thatcontains the transportation facility).

Referring to FIG. 2, arrays 124 such as those described in connectionwith FIG. 1, each containing a plurality of modules 110, may in turn beconfigured into a plurality of arrays 124, arranged with respect to eachother and oriented with respect to a direction of fluid flow. FIG. 2shows one possible view of four arrays 124 configured in a checkerboardpattern, which is one preferred embodiment of a grouping of arrays 124.In embodiments, arrays 124 may be arranged in a number of combinations,such as the checkerboard described herein, which may use a matrix todivide a given site. One option may be a diamond pattern with spacingranging from the 1×1 checkerboard implementation to an n×mimplementation where the 1-n may refer to the number of cells by whichthe diamond is formed. Another option may be a curved arrangementwherein the rate of curvature can range from 0 to 1 with the spacingstructure ranging from 1 to n. Alternatively the matrix may be filledcompletely dependent on the particular properties of the arrays deployedin the formation. Additionally the arrays may be co-mounted on singularsubstructures in any of the distributions of machines described herein.In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array maybe configured with arrays located in a matrix arrangement with aplurality of similar arrays, such as embodied in a checkerboard pattern,a diamond pattern, a regular pattern, an irregular pattern, a curvedpattern, filled pattern, and the like.

As shown in FIG. 3, the n×m modular array 302 may be comprised of ascalable modular networked superstructure providing both support for atleast one module and the facility for power control, management, andcollection of power from individual modules, and conversion and transferof said power to either a plurality of storage units, a grid, or acombination thereof. In embodiments, the present invention may providean array of nozzles adapted to generate electrical power from the flowof air, where the array may be supported by a scalable modularsuperstructure. The superstructure may be a modular assembly employing ashape such as a space frame type, geodesic, orthogonal, and the like.The superstructure may be of a nozzle-structural integrated type, suchas a flexible pressure based integrated structure, a rigid cellintegrated structure, and the like. The superstructure elements may beconnected by a connection facility such as a weld, a glue, a contactfusing facility, a locking mechanism, and the like. In embodiments, thesuperstructure may include structural components and connectors whichcan be assembled on-site. The superstructure and its elements may have acomplex local and global 3 dimensional topography, such as to maximizeload bearing properties, minimize material use, minimize materialweight, and the like. Structural members of the superstructure may havea uniform circular profile, polygonal profile, elliptical profile,square profile, triangular profile, n-pointed star profile, and thelike. Structural members of the superstructure may have a variableprofile, such as with linear scalloping, radial curvature variability,elliptical curvature variability, square variability, and the like. Themembers of the superstructure may be an isotruss type variable soliditystructure. The elements of the superstructure may include at least oneof a polymer, composite, metallic foam, composite foam, alloy, and thelike.

FIG. 4 shows an embodiment of a complex topography connector and members402. In embodiments, this may provide an example of complex moldtopography intended to reduce material use and maximize structuralproperties, and take the form of surface structures, profiles, variablesolidity structures, and the like.

FIGS. 5A and 5B show embodiments of structural members 502A and 502B.These examples may be of structural members of variable density andprofile. These may represent a subset of possible complex topographymembers. For example, the member 502A one on the left may be made byfilament winding, and the member 502B to the right may be extruded ormolded fiber reinforced plastic.

FIGS. 6A and 6B shows an embodiment of linear scalloping, such as for awall nozzle, structural member, and the like. This may provide a complexwall for the nozzle, structural member, and the like. The depiction oflinear scalloping 602A to the left represents a scalloping surfaceorientation, and the depiction of linear scalloping 602B to the rightrepresents the scalloping in a profile view.

The superstructures, may be self-orienting (such as due to the shape ofthe nozzle) and may include methods or systems to mechanically (asdescribed herein) or otherwise control the orientation of the array, orof a module within the array, with regard to the direction of the fluidflow in a fixed implementation. Methods of mechanical orientation mayinclude yaw motors, stored energy flywheels, and the like, or othermethods known in the art. Alternately, they may be mounted onto a mobileplatform to seek out optimal flow conditions. In embodiments, thepresent invention may provide an array of nozzles adapted to generateelectrical power from the flow of air. The array may includeself-orienting nozzles, self-orienting nozzles configured with anon-mechanized element that uses airflow to orient the nozzles,self-orienting nozzles with independent orientation at differentlocations in the array, and the like. The array may include a nozzlecapable of orientation to a vertical component of airflow. Inembodiments, the present invention may provide a nozzle adapted for usein a wind power generating turbine. The nozzle may be configured to becapable of orientation to a vertical component of the wind. In addition,the nozzle may be self-orienting relative to the direction of the wind,such as when there is a tail on the nozzle.

The superstructure may be supported by a number of methods and systemsdepending on the nature of the flow, such as floatation suspension,tower/towers, building integration, cable suspension, and the like.Additionally arrays may be fabricated of materials that enable a lighterthan air implementation. In embodiments, the present invention mayprovide an array of nozzles adapted to generate electrical power fromthe flow of air, where the array may be supported by a scalable modularsuperstructure. The superstructure may be a suspension type ofsuperstructure, supported by a lighter-than-air mechanism, and the like.In embodiments, the present invention may be mounted on land or at sea,attached to existing structures such as a building, bridge, tower, andthe like, or stand alone as a dedicated structure.

The superstructure may be executed as a separate modular supportstructure inclusive of the method of load bearing and powerdistribution. The superstructure elements may also be integrated intothe nozzle structure such that the module becomes a wholly containedelement. In this case the preferred superstructure may provide acolumnar method of plugging the integrated module into the power system.In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may be supported by a scalable modular superstructure. Thesuperstructure may be of a variable type, such as with regard to loadbearing properties, structural properties, and the like. The elements ofthe superstructure may be of a uniform type with regard to load bearingproperties, structural properties, and the like. The elements of thesuperstructure may be variably adapted to the lowest cost solution forlocal load bearing parameters within the array. In embodiments, thesuperstructure may be rigid, may have global flexing mechanisms toaccommodate live loading, may have local flexing mechanisms toaccommodate live loading, and the like.

As shown in FIG. 7 and FIG. 8, the array implementation may providevarious advantages. First it may allow the modules to cover any givenarea without being subject to the inefficiency introduced by the lengthof an efficient divergent component. Secondly the implementation neednot be uniform as in a horizontal-axis wind turbine (HAWT). By housingthe n×m modular array in such a superstructure, the structural upperlimit of flow area or plane a system can cover and gather energy frommay be substantially increased. By covering, say, a rectangular area,the upper rows of an array may be producing energy, if wind is themedium, potentially at a substantially faster mean velocity than lowermodules (because the wind is greater at the top of the array than it iscloser to the ground). This means that in addition to the increasesengendered by the modules, the array structure itself may engender anincrease. In this regard, if the medium is wind, a structure wherein theheight is greater than the width may be the most efficient use of theplane for energy production with the multiple of power productionincreasing as the height value increases from a baseline wherein theheight value is less than the width value. For example, both FIG. 7 andFIG. 8 depict a HAWT 702 that has a 75 meter diameter circular sweeparea of approximately 4400 sq. m., and with a hub height of 50 m with awind speed of 6 m/s. In FIG. 7 the array implementation 704 has anequivalent swept area provided with a 50 meter wide array area with thelowest row at 30 meters and wind speed of 5.4 m/s, and an upper row at117 meters with a wind speed of 7.6 m/s. In FIG. 8, the same swept areais accommodated with an array implementation 802 of the same lowerheight and wind speed, but this time with a narrowing 44 m width andhigher upper row, now with an elevated wind speed f 8.1 m/s. Inembodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array maybe of variable width at different heights. The depth of the array may beless than or equal to the width of the array, such as greater than orequal to the width of the array, more than about 1.25 times the width ofthe array, more than about 2 times the width of the array, and the like.

In this system the dynamic pressure acting on the structure may bedistributed equally through the structure as opposed to being focused ona propeller root or tower as in most horizontal axis machines therebyexpanding the overall swept area that can be covered per linear foot ofmachine width. Additionally, nozzle efficiency may reduce dynamicpressure on the structure. The determination of the number of modules ina given array implementation may be predicated on the necessary nozzlelength ratio, structural loading, and desired energy output.

Some array geometries, such as rectangular/square, triangular,trapezoidal, or a combination or inversion thereof (e.g. and invertedtrapezoid or a hexagon), in the x,y dimensions may maximize wind planeusage relative to cost. Note that a non-uniform x,y implementation wouldalso fall within the scope of the present invention. Structure in the zdimension may be implemented as a uniform or non-uniform plane, withcurvature either of equal or variable depth, or the like. An array ofdimensions wherein said wind facing plane is equal to or greater thanthe depth may provide improved performance in terms of area utilization.In embodiments a configuration wherein the flow-facing width of themachine is greater than depth may provide similar plane coverage asfreestanding rotor systems.

FIGS. 9A and 9B depict a series of arrays side and front elevations 902Aand 902B. In addition, superstructures may be mounted to a platformsingly or in series in the z dimension.

Modules mounted in the superstructure may be comprised of a nozzleconfiguration, a single or plurality of energy capture device/s, asingle or plurality of flow enhancement surface structures, and thelike. The modules and modular elements of the superstructure may be“plug and play” devices allowing maintenance or refitting of the arraycomponents to be performed on- or offsite.

Module nozzle geometry may be optimized, based on uniqueintake-to-throat geometry, exit geometry, volumetric ratios, and arevised theory of fluid dynamic forces, to maximize plane usage,minimize forward and inlet overpressure, entrain and accelerate highpercentage flows with at least one optimized fascia to maximize flowestablishment, and the like. The nozzle may further be of variablegeometry to adapt velocity conditions in the nozzle configurationrelative to ambient velocity conditions and help stabilize said velocitywithin a desired operating range. The variable intake geometry andnozzle configuration geometry may be executed as a single fascia or witha plurality of dependent and independent fascia depending on module sizeand/or the properties of a given fluid. In embodiments, the presentinvention may provide an array of nozzles adapted to generate electricalpower from the flow of air. The array may include nozzles of variablesize, nozzles of variable type, and the like. For instance, variationmay relate to constriction rates of the nozzles and or the powergeneration characteristics of the nozzles. The array may include nozzlesof a shape represented by truncation of a catenoid and the nozzlesshaped to facilitate air flow at the entrance of the nozzles. The arraymay be a packed array of nozzles of variable intake shapes, such ashexagonal intake shapes, triangular intake shapes, square intake shapes,octagonal intake shapes, and the like.

Nozzles additionally may be implemented in either single or multistageconfigurations inclusive of reaccelerating or pressurizing a fluid flowwithin or exterior to the module for additional use in energyproduction. Both uniform and non-uniform execution of the array withregard to nozzle geometry and constriction fall within the scope of theinvention. In embodiments, the present invention may provide an array ofnozzles adapted to generate electrical power from the flow of air. Thearray may include nozzles configured in series relative to the directionof airflow, configured in a nested series, and the like.

Module energy conversion may be comprised of a plurality of kineticenergy conversion devices, such as single or multi-blade rotors, orother facility for kinetic energy conversion, coupled with a facilityfor producing a usable form of power such as a generator, a transmissionand a generator, multiple generators and a usable form of powerelectronics, and the like, to control the loading parameters under whichthe conversion facility operates and to convert or condition the powerproduced into a usable form by whatever end-use facility may beintended, such as a local grid, national grid, storage, or the like. Inembodiments, the conversion may be devices adapted specifically to theoptimized and variable properties of the nozzle configuration and moduledesign, wherein the KE conversion and energy producing devices may beintegrated to the particular parameters of an embodiment to optimize useof the flow.

To maximize energy production relative to cost across a broad range ofwind velocities, a variable blade number rotor may be used as the methodof kinetic energy (KE) conversion. In the case of a variable bladenumber rotor, a self- or mechanically folding blade design may be used,wherein the number of blades is reduced by slotting a divisible numberof blades into the preceding blades in the series. Rotors with differentnumbers of blades and different profiles may have performance profilesthat closely fit a given flow velocity range. Since it is desirable tooptimize the power output of a flow driven power device, a rotor thatadapts the disc solidity presented to the flow may be more efficient atgathering power in the lower speed regimens, and/or under high loadconditions, than a fixed solidity rotor. A variable solidity rotor mayhave a plurality of prime number rotors sets, for example 2, 3, 5, andthe like. Rotor sets may be mounted to a series of dual position sliprings wherein when the dynamic force on a given set is exceeded the ringmay be released and dynamic force on the blades may shift it to a closedposition on the following set of blades. In embodiments, a mechanism maybe slotted on closure such that when the dynamic force on the closedblade sets indicates a drop in velocity the blade set is released toopen position. In embodiments, the present invention may provide anarray of nozzles adapted to generate electrical power from the flow ofair. In embodiments, a rotor may be configured to operate within a windpower generating turbine, where the rotor is configured to present avariable number of blades. In embodiments, the number of blades onrotors of nozzles of the array may vary from one nozzle to other nozzle.

Additionally an “inertial” rotor is described wherein the rotationalmomentum of the blades may be manipulated to alter the inertia of rotor.

Additionally the rotor generator relationship may be executed as in aHAWT wind turbine, with the generator or generators receiving theirmotive force from a central shaft either directly or through a geareddesign, as a fully integrated implementation, as an integratedcomponent, and the like.

In a fully integrated implementation the nozzle itself may constitutethe generator, wherein the rotor blades may be manufactured as induced,excited, permanent magnet rotors, or with a magnetic fluid such asmagneto-rheological fluids and the stator is integrated into the nozzlemold, and the like. An alternative implementation may be one wherein therotor is attached to a magnetic bearing of the same diameter as thethroat to generate power. Another may be the rotor attached to a bearingof the same diameter as throat that is geared on the outward face todrive a plurality of generators surrounding the throat area.

Pressure gradient (PG) enhancement devices/techniques may be usedthroughout modules and the superstructure to perform the task of bothlocal and global gradient enhancement with respect to flow through themodules and superstructure. PG enhancement may be performed by utilizingproperties of thermo and fluid dynamics to create regions of additionalfluid sparsity thereby engendering enhanced local and global gradientdifferentials and allowing the establishment of higher percentage flowsthrough a given module configuration. In addition, a method of achievingdirectional suction pressure may also be used to enhance the rate ofsystem flow.

Due to the wake profile of the nozzles they may be placed in a wind-farmarray in a series of more efficient patterns than is possible withcurrent generation technology, as described herein. For instance, afilled or binary checkerboard pattern may maximize cost to benefit andland use. Additionally, a method of efficient energy storage andintegration of buildings and arrays is disclosed herein.

FIGS. 9-22 depict various aspects of the invention. FIG. 9 depicts aseries of arrays side and front elevations 902A and 902B. FIG. 10depicts non-uniform array with orientation tails in side elevation1002A, top view 1002B, and front elevation 1002C. FIG. 11 depicts anarray 124 with nozzles 104 including three integrated generators 1102.FIG. 12 depicts an integrated generator 1102—module 104 example, wherethe nozzle may include PM turbine blades/rotor and exterior stator. FIG.13 depicts an array with storage 1300, including a pressure vessel 1302,fluid turbine 1304, fluid containment 1308, vortex tube 1310, flowchamber 1312, and turbine compressors 1314. FIG. 14 depicts a module ina triangular superstructure 104. FIG. 15 shows details the majorcomponents of an example nozzle 104, including the inlet screen 1502,inlet 1504, rotor 1508, transmission/generator 1510, supports 1512,control and management 1514, diffuser 1518, and exit screen 1520. FIG.16 shows two nozzles 104 in a serial arrangement 1602. FIG. 17 depictsan embodiment of a front and side elevation of a hexagonal nozzle 1700.FIG. 18 shows an example of a nozzle with circular throat and polygonalexit 1800. In this example, a nozzle with a circular throat mayinterpolate from 1/r curvature at the throat to 0 curvature at thepolygonal exit. In embodiments, intervening slice polygons may beReuleaux polygons. FIG. 19 shows and example of two nozzles 104 nestedtogether 1900, where splitting the rate of constriction between the twonozzles and nesting the smaller nozzle into the larger may increase theacceleration. FIG. 20 depicts a front view of a superstructure connector2002A and a side view of a superstructure connector 2002B. FIG. 21depicts a horizontal axis wind turbine generator arrangement 2100 withmodule protection screen mounts. FIG. 22 depicts a superstructure andmodule arrangement 2200 for hexagonal modules.

The module may be an important aspect of the invention, where a modulemay be an integrated element that is inserted into the array as a plugand play component. The module may be comprised of structuralcomponents, nozzle fascia, rotor, generator, transmission, powermanagement components, and the like. A module may be assembled aselements that fit separately onto a given superstructure cell. Themodule may have at least one automated locking/unlocking mechanism thatmay attach said module to both the superstructure and its neighbormodules. This may allow single modules to be removed and replaced atneed without effecting the operation or structural integrity of thearray.

In embodiments, the module may have at least one structural componentthat provides support for the main nozzle surface, including support andprotection for the power components. The structural components mayconstitute the main load- and pressure-bearing components of the array.Additionally they may include bundled power management and transfercomponents that connect into the main power conduit array.

In embodiments, an inertial rotor may manipulate rotational momentum toprovide variable rotational inertia by way of a variable radiusweighting system, where the rotor blades and hub may be comprised of asingle or plurality of staged chambers. In addition, a weighted materialmay be allowed to move based on centripetal motion toward the outerradius. This may be executed with a weighted material that may becontrolled in its balance under rotation. In the case of a fluid, thefluid may be allowed to cycle through a series of chambers therebycreating a more stable inertial rotation and energy output. Thisinertial rotor may also be executed by way of weights and flexiblestructures, such as springs, memory plastic, and the like, where theflexible structure and weight may be slotted into a single internalchamber in the rotor blades. As rotation and centripetal force increasethe weight may extend the flexible structure to the tip of the rotor andthereby change the inertia of the rotor to a more optimal profile forthe rotor's use. Weights or fluids may also be controlled by way ofactuators. In embodiments, the weighted material may be maintained at anextended position during certain conditions, such as when fluid forcesare falling off, when fluid forces are leveled off, when fluid forcesare at a maximum, and the like, where the extended position may be amaximal rotation position. In embodiments, the present invention mayprovide an array of nozzles adapted to generate electrical power fromthe flow of air. A rotor may be configured to operate within a windpower generating turbine, where the rotor may be configured to havevarying amounts of inertia, such as the rotor including a blade on aspring to provide varying inertia at different rotation speeds, therotor including a fluid component internal to a blade to providevariable inertia, and the like.

In embodiments, the nozzle portion of the module may be important inpower production. Nozzle types for manipulating the fluid flow mayinclude solid body w/single fascia, solid body w/ plurality of fascia,partially open body geometry, and the like. There may be differentiatingcharacteristics to the underlying geometry of the nozzle. To optimizeplane use a quadric surface geometry may be utilized where the inlet ofthe nozzle is formed by the truncation of a radial or radial/ellipticalfunction at a polygonal boundary. This may allow the nozzle to cover apolygonal intake area with variable intake curvature while having aneffective momentum focusing circular structure and expanding to aclosely similar polygonal outlet area. The ability to cover anon-circular, for example a square inlet area, may yield a moreefficient use of the fluid plane, and the quadric geometry may maximizefascia separation and minimize overpressure relative to the throat.Additionally, the complexity of the surface geometry may be extended byapplication of quadric or radial structures to the underlying geometry.

A second characteristic may be the radial function used to determine thecurvature of the constrictive region conforms. The optimal curvature inthe prior art for a radial nozzle may be an arc section from a circle,such as between 1.8 to 2 d, where d is the diameter of the throat. Suchcurvature may engender the loss of a large portion of the mass availableat the intake area.

In embodiments, different types of single arc and multi-arc curvaturesmay be used depending on the level of nozzle constriction, such as asingle arc radial or elliptical curvature used for exclusively lowconstriction rates, a single arc intersection of two radial functionsused at low or medium rates, a single arc execution based on an arcproportion determined by the vector interpolation of momentumdistribution described in the method section of this invention, multiarc and single-body or multi-body fascia for higher constriction rates,and the like. This curvature may also vary depending on its angularposition relative to bounding polygon and the center of the throat.

In embodiments, the divergent geometry in configurations of the currentinvention may be predicated on a ratio of rate of constriction to intaketo divergent section that results in a volumetric ratio function of theconvergent volume to the divergent volume wherein the volumetric ratioincreases with the rate of constriction. As an example, a 2×constriction may require a volumetric ratio in excess of 1:7, whichgiven the parameters described in above with regard to constriction mayresult in a less than 4 degree divergent angle. Additionally a variablenozzle may provide a constriction rate of the nozzle dynamicallyadjusted to the flow velocity to maintain velocity within the module ata given rated speed. This may allow the reduction of variability in thewind resource and allow the array to output at a given ratingconsistently.

In embodiments, the array superstructure and array installation may beprovided, where the array superstructure may be comprised of powertransfer and management and control components, module structuralsupport elements, the array support structure, and the like. Powertransfer components may be bundled into the modular structural supportcolumnar elements extending from the top to the base of the array andallowing the module power systems to transfer power with a minimumnumber of connections and resistance. The superstructure may be eithercentralized, such as with a mast and boom structure, or distributed,such as with multiple columnar supports.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includenetworked or distributed power control and transfer. The power controlmay optimize the power production within a plurality of nozzles and maymonitor power production for performance, maintenance, replacement, andthe like. The power control may dynamically manage load requirements fora plurality of nozzles, such as when the management is local, global,and the like. The power control may optimize performance through use ofneural networks, genetic algorithms, fuzzy algorithms, probabilisticpredictive-corrective feedback loops, and the like, to maximize outputand minimize losses. The power control may use a dedicatedcommunications system, routing system, distributed communicationssystem, and the like, to control individual elements within a pluralityof nozzles. The power control may utilize digital electronics, analogelectronics, an electronics chip, electronics logic gates, centralizedprocessing, parallel processing, distributed processing, be hard-wired,wireless, and the like. The power transfer may be integrated intostructural components, external to structural components, and the like.The power transfer may include topography that may minimize resistancelosses, such as with a branch-trunk network structure, a directgenerator-main trunk connection structure, and the like. FIG. 23 depictsa space frame for a square array in two different configurations 2302Aand 2302B. FIG. 24 depicts nozzle polygons with different entranceshapes with embedded structural members 2402A and 2402B, where the viewto the left shows a larger structural member embedded, and the view tothe right shows a smaller structural member embedded. FIG. 25 shows apower transfer arrangement 2502 in a square array showing the powertransfer structure with nozzles in place. This may depict an example ofa modular implementation where the horizontal structural member isembedded in the module and then locks into the columnar component toform the space frame. Other embodiments of this may include a clamshellapproach, direct assembly, and the like. FIG. 25 also shows a transferjoint with 35 kV main columnar cable 2504 connection, 25 kV generatorcable connection 2508, and connector plates 2510.

In embodiments, the superstructure configuration may be based on aparticular array implementation. Array implementation may follow anynumber of geometries based on module geometry, such as hexagonal,rectangular, triangular, trapezoidal, and the like, where array geometrymay not be dependent on module geometry. Array rows may additionally bemounted individually to allow individual row response to wind direction.These rows may be mounted on individual bearings, or the like, of thetypes described herein, or may be mounted centrally to a column wherethe outer fascia of the column and the inner fascia of the row may bemade up of the materials as described herein with reference to amaterial properties bearing. In such cases each row may be fitted withmechanical or flow based orientation mechanisms. Each array layer mayadditionally be executed with power management suited to the conditionsat array height, to increase overall output, to stabilize said outputbased on variation of power curve and dynamic loading as a function ofincreased velocity w/increased height, and the like. In addition, thesupport structure may be executed as either a central column or a seriesof columns. In the case of a series of columns, a number of machineplacement configurations may be used to maximize land use vs.installation output. For instance, a checkerboard or filled matrixconfiguration may be preferred wherein the foundation pilings are sharedbetween arrays at each intersection of the grid to optimize the yield toinstallation cost ratio.

In association with the installation, energy storage may be provided.Due to the variability of the resource it may be desirable to have acost-effective method of energy storage for a wind energy machine.Compressed air or pumped hydro storage or batteries or other facilitiesfor storage as are known in the art may be a cost effective way to storewind-produced energy wherein the energy produced by the array may beused to compress air or pump water up a gravity gradient. The storedenergy may then be used to power a turbine that produces energy basedupon grid demand not wind variability. A major problem with some storagesolutions is efficiency relative to cost. In the case of hydro theenergy storage requires a large facility and availability of water toaffect storage. For this reason compressed air may present a moregenerally applicable solution with fewer requirements in terms of spaceand construction. For instance, compressed air and vortex tubes may beused to create a density based closed loop flow system from which energycan be gathered, where vortex tubes can be used to separate flows intothe energetic and non-energetic components with an input of compressedair. Depending on the pressure of compressed air, temperature outputsbetween the hot and cold outputs of the vortex tube can be substantial,on the order of 100C or more. As in a basic engine schematic, theseoutputs may be used in a closed loop system to create a hot and coldsink wherein the rate of flow may be determined by the temperaturedifferential between the sinks While the energy contained in the rawflow is still inefficient with regard to amount of energy used tocompress the source gas, the introduction of optimizedconvergent/divergent (C/D) nozzles may provide a way to artificiallyincrease the amount of kinetic energy present at the point of conversionin the closed loop flow and thereby the amount of power recovered fromthe storage process.

In its simplest form, the storage/recovery device may include methods ofpressurizing the preferred medium, a pressure vessel for storage of thecompressed medium, a secondary external pressure vessel to recapturethermal energy released by compression with a method of controlling theflow to the turbine, a controlled valve to release the pressurizedmedium in the primary vessel based upon grid demand, at least one vortextube, a flow chamber, a facility to channel or transfer thermalproperties of the hot and cold streams into the flow chamber, aplurality of embedded nozzles within the flow chamber to increaseproportion of kinetic energy in the flow, a facility to control andmanage the power derived from both pressure systems, a facility togather all resultant KE and transfer the power to the grid, and thelike. The baseline KE and thermal energy that drives the system may becaptured through use of additional turbines such as a steam turbinederiving steam pressure and flow from heat given off by the pressurevessel during the air compression phase or KE turbine capture of theenergy of the fluid flow used to drive the closed loop system.

In embodiments, the present invention may include a plurality of processand functional components, such as orienting the array, a nozzle foraccelerating the air into the array element, a rotor motor that convertsthe kinetic fluid energy into mechanical energy, a gear box fortranslating the mechanical energy into usable rates or controlling theload applied to a facility for KE conversion allowing the energyconversion process to operate at in an optimal range, a generator toconvert the mechanical energy into electrical energy, energy storage, afacility for converting or conditioning the energy produced into adesired form, a substation and grid interface, fuel cell loading, andthe like. In embodiments, storage of energy may be taken from after thegenerator in the form of electrical energy, or before the generator inthe form of mechanical energy such as described herein. The array may beused in a direct energy transfer system, such as for pumping water,milling, pumping oil, pressurization, gas pressurization, hydrogenseparation, fuel cell loading, and the like. Mechanically, the presentinvention may include a plurality of components, such as the modulesthemselves, arrays of modules, arrays and arrangement of arrays, thesuperstructure, bearings, and the like.

In embodiments, the module or array may be provided with a way to orientitself relative to the fluid flow. For instance, a tail may be providedto self orient the structure, such as a tail placed on a rotatingsupport axis that spins the module or array to the wind's direction, orthe structure of the nozzle or the array may be constructed in such away to engender more orienting properties. There may also be otherconfiguration features that contribute to orientation, such as throughside cladding shape, providing different orientations at differentlevels, allowing different levels or modules or array segments to orientindependently, and the like.

In embodiments, the nozzle's configuration may provide an importantelement of the invention, such as a 2.75 constriction nozzle producing a6 to 7.5× power increase, and the like. Mass flow rate may be affectedby a number of parameters, such as rate of constriction, includingintake geometry and diffuser geometries being very sensitive to rate ofconstriction—as you move from 2 to 2.75, effects may become much moresensitive to things like the intake angle; past simple geometries,second order equations—may become very complex, where more complexgeometries and surfacing may become an effect; and the like. Inembodiments, a rate of constriction of 2.75 may be a good value, wherethe relationship of rate of constriction, curvature, length of diffuser,intake, etc. may be sufficient to achieve a large power increase withoutrelying on a complex geometry. With a constriction rate below 2 timesthe realized power increases might not be sufficient to provide anadvantage against HAWT systems with regard to a comparison of swept areaused by the whole machine and the relationship between cost and yield.Variable throat constriction may be a factor, with the ability to varythe throat. Temperature may be a factor, where heating the air or othermethods of creating additional sparsity rearward of the nozzle maycreate an improved flow, and may also be effective in a storage system.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may include aconstriction. For instance, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2and where the length of the diffuser is more than five times the lengthof the intake, and where the ratio of the diffuser length to the intakelength may be about 7:1. In embodiments, the constriction ratio of thediameter of the throat to the diameter of the intake may be more than 2and where the nozzle is used in an array of nozzles, or as an individualnozzle. In another instance, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2.5and where the length of the diffuser is more than five times the lengthof the intake, and where the ratio of the diffuser length to the intakelength may be about 9:1. In another instance, the nozzle may include aconstriction ratio of the diameter of the throat to the diameter of theintake of about 2.75 and where the length of the diffuser is more thanfive times the length of the intake, and where the ratio of the diffuserlength to the intake length may be about 11:1. In another instance, thenozzle may include a constriction ratio of the diameter of the throat tothe diameter of the intake of more than about 1.5 and where the lengthof the diffuser is more than five times the length of the intake. Inembodiments, the nozzle may include a converging intake and a divergingdiffuser, where the length of the diffuser may be longer than theintake, such as more than five times the length of the intake. Inembodiments, a nozzle may be adapted for use in a turbine for generationof power from ambient movement of air, where the nozzle may include anintake and a diffuser and where the length of the diffuser is longerthan the intake, such as more than five times the length of the intake.

Nozzle intake geometry may also play a key role in the presentinvention, such as in the leading edge geometry, curvature, length ofintake, exit geometry, and the like. The curvature of the intake may beimportant, such as when the average angle is greater than 45 degrees ina two times constrictor, then you might get a power loss. Once you go upto a 2.5 rate of constriction, then you may become much more sensitiveto curvature and length of intake. Length of the intake may beimportant, such as in the time that the gradient has to act on the flow.If intake length exceeds the throat by a significant factor, there maybe loss. Once intake length is less than the throat length, thensuddenly you may see the actual predicted velocities at the throat. Notethat if elastic collisions are assumed, momentum may deflect from theleading edge. It may not conform to that, nor to a classic boundarylayer problem. The effect of momentum deflection may be greater thananticipated by a momentum diffusion layer analysis. There may be somekinetic energy exchange with the wall that slowly turns with the intake.Looking at sparsity and density of molecules and delta of momentum basedon probabilistic movement of molecules in the sparse direction may beprovided. The lower rate of constriction, the shorter the intake lengthmay have to be. With an initial sparse gradient, if there is a properintake angle that allows momentum to be directed toward the throat, adensity increase may be experienced in the region of the intake. Whenthere is an incorrect intake geometry at a higher rate of constriction,a toroidal bleed-over on the leading edge may result in mass loss to theexterior of the nozzle.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, such as optimized for leadingedge geometry, for curvature, and the like. The leading edge of thenozzle may be optimized based on the angle of incidence to the directionof the flow, where momentum vectors derived from the leading edge maygenerally clear the throat of the nozzle. In embodiments, the intakeleading edge may have an angle of incidence of no more than 1.1*0.5*θ,where tan θ=(0.5(D_(I)−D_(t))+D_(t))/I₁, and where D_(I) is the nozzlediameter at the intake, D_(t) is the diameter of the throat, and I₁ isthe intake length. In embodiments, the present invention may provide anozzle adapted for use in a wind power generating turbine, wherein thenozzle is optimized based on intake length, leading edge shape, diffuserlength, and the like. In an example, for a nozzle where the area at thethroat is ½ the area of the intake and the intake length is ½ thediameter of the throat, the maximum incidence angle at the leading edgemay be 47 degrees. In embodiments, the optimal range may fall between 41and 37 degrees for 2 times constriction for this set of parameters. Theintake may conform to an elliptical, radial arc, a combination of thetwo, a combination of a plurality of elliptical or radial arcs from theleading edge to the throat, and the like. In embodiments, the nozzle maybe optimized based on an intake length to divergent length ratio wherethe intake length may be equal to or less than the diameter of thethroat.

In embodiments, the initial intake momentum vector may be depictedgraphically. FIG. 26 shows a diagram depicting an initial intakemomentum vector 2600, which may be related to the formula for derivingthe minimum leading edge angle. In the diagram, the incident path andincident momentum vector are shown relative to the intake curvature, theincident wall, and the opposite throat wall.

In embodiments, the design of the intake geometry may result in anon-perfect angle with relatively short diffuser. A 4× power increasemay result with a 45 degree intake angle, as long as there is curvature,where curvature spreads the force acting against the flow. A basicnon-symmetric catenoid (rotated hyperbolic function) may be used. Toachieve an array you may artificially truncate the catenoid (taking afunnel/catenoid) and truncating with a hexagon, square, triangle, orother polygon. In using a hexagon, there may be more exterior angularlatitude, but straight corners may have to be more curved. Surfacing maybe a factor, where there may be small vortex generators on leading edgesor over the entire nozzle surface, such as square vortex generators,golf ball dimples, or any surface that creates a thicker displacementlayer, but relates to the boundary layer better. In embodiments, thepresent invention may provide a nozzle adapted for use in a wind powergenerating turbine. The nozzle may include a diffuser, the cross-sectionof which may have substantially linear sides from throat to exit. Inembodiments, the exit angle of the diffuser may be less than about fourdegrees. The nozzle may have a facility to generate a voracity or swirleffect proximal to the exit of the diffuser, such as where the diffuserincludes a vane to facilitate the effect. In embodiments, the nozzle mayhave a diffuser, such as a diffuser with a polygonal exit shape, asquare exit shape, having symmetric polygonal walls, having symmetricpolygonal walls that are truncated, and the like.

In embodiments, low cost materials for nozzles may be a factor, where ifthere's an efficient pass through, the whole thing orients itself (actslike a big tail on a kite). Once you break into arrays and optimize, youmay not need materials such as carbon fiber, eGlass, and the like, butvery low-cost, lightweight materials may be used, especially at the topof the superstructure/array, such as a polycarbonate thermofoam, and thelike. A combination of inexpensive and expensive materials may also beused wherein the mechanical properties of a fiber in combination with aclosed or open cell foam may result in an overall cost reduction. Inembodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. The array mayinclude nozzles made with polycarbonate thermofoam, polymer, afiber/resin composite, a syntactic foam, a closed cell foam, an opencell foam, with gelcoat, and the like. In embodiments, the presentinvention may provide a nozzle adapted for use in a wind powergenerating turbine. The nozzle may include at least one of a pluralityof mass produced components. The components may be manufactured throughrotomolding, injection molding, scrimp molding, thermoforming, lay-up,vacuum molding, filament winding, and the like. The materials used inmanufacturing the components may include acrylonitrile butadiene styrene(ABS), polycarbonates (PC), polyamides (PA), polybutylene terephthalate(PBT), polyethylene terephthalate (PET), polyphenylene oxide (PPO),polysulphone (PSU), polyetherketone (PEK), polyetheretherketone (PEEK),polyimides, polyethylene,polypropylene, polystyrene, polyvinyl chloride,polymethyl methacrylate, polyethylene terephthalate, and the like. Thematerials used in manufacturing the components may include at least oneof acrylic, aramid, twaron, Kevlar, technora, nomex, carbon, tenax,microfiber, nylon, olefin, polyester, polyethylene, dyneema, spectra,rayon, tencel, vinalon, zylon, asbestos, basalt, mineral wool, glasswool, syntatic foams, carbon foam, polyurethane foams, polystyrenefoams, metal foams, and the like. The components may be designed toenhance the structural properties of the nozzle to provide reduced costof material, reduced weight of material used, minimized assembly time,minimized transport costs, and the like.

In embodiments, drill-throughs may be a factor, where a drill may gothrough from the outside to increase the flow from an ambient outsideair, or perform vaning with drill-through to introduce the ambient airand change swirl. In embodiments, the present invention may provide anozzle adapted for use in a wind power generating turbine, where thenozzle may include a through-hole to facilitate air flow.

In embodiments, more complex intake geometries may be a factor, such ascombinations of geometries, truncating a catenoid with a polygonalshape, taking a quadric function and applying it on an ellipse to thesurface creating aerodynamic shapes that channel well (e.g., sharkscales, single or multi-layer scalloping, whale fin, and the like),extending quadric truncation onto the surface of the nozzle spreadingthe momentum from off of the leading edges and bringing in the intakestream into a less oppositional mode, a series of linearly ororthogonally concave curvatures onto a convex shape, applying to thewalls at a larger scale, vortex generators within the nozzle itself(e.g., squares, dimples, vortex film, and the like), forward wedging tochannel the flow toward the throat, concave and convex curvature, splitdiffuser in half rearward of the throat, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may have a leadingedge and an intake curvature between the leading edge and a throat ofthe nozzle, where the leading edge and intake curvature of the nozzlemay be adapted to focus momentum vectors of air particles in the intakeregion to facilitate air flow within the nozzle. In embodiments, thenozzle may have a leading edge and an intake surface with an intakecurvature between the leading edge and a throat of the nozzle where theleading edge and intake curvature of the nozzle are optimized based onthe predicted gradient of air particles within the nozzle, the predictedenergy transfer of air particles in interaction with the intake surfaceof the nozzle, the predicted focus of momentum vectors of air particleswithin the nozzle, and the like. The nozzle may have a leading edge andan intake length between the leading edge and a throat of the nozzle,where the intake length of the nozzle may be less than the diameter ofthe throat of the nozzle, such as by two times. In embodiments, theintake length may be less than the diameter of the throat, betweenone-half and about equal to the diameter of the throat, and the like.The geometry of the nozzle may be adapted based on calculation of theprobability of movement of air molecules from dense to sparse regionswithin the nozzle. The surface of the nozzle may include a vortexgenerator. The nozzle may be configured with surface shaping to optimizeflow from the leading edge, such as based on quadric truncation of anellipse, multiple quadric functions similar to an n-iteration fractal,shark scale shape, scallop scale shape, whale fin shape, and the like.

In embodiments, nozzles may be in series, such as nesting nozzlesrearward of the throat, where the one in the throat may come very closeto a theoretical level of increase, and the outside one may get 90% ofits theoretical level of increase. In embodiments, the nozzle module maybe integrated as one piece, such as making the blades of the rotor ofthe turbine an integrated component. Other less optimal forms may alsobe used and combined into an array such as super-venturi's, wide-anglediffusers, two dimensional nozzles, flat wall nozzles, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may have an intakegeometry configured to optimize airflow based on momentum vectors in theintake region, where the momentum vectors may derive from interactionwith the angle of the leading edge of the nozzle, the nozzle may beconfigured to generate momentum vectors that are directed to clear thethroat of the nozzle after interaction with the leading edge of thenozzle, and the like. The nozzle may be arranged in series with at leastone other nozzle. The nozzle may be formed with a constriction ratiobetween the intake diameter of the nozzle and the throat diameter of thenozzle, such as about 2.75, between 2 and 4, between 2.5 and 3.5, andthe like. In embodiments, the nozzle may include a constriction ratio ofthe diameter of the throat to the diameter of the intake of about 2 andwhere the length of the diffuser may be about seven times the length ofthe intake. In embodiments, the nozzle may include a constriction ratioof the diameter of the throat to the diameter of the intake of about 2.5and wherein the length of the diffuser is about nine times the length ofthe intake. The nozzle may be configured with the capability to vary thediameter of the throat. In embodiments, a facility may be provided formodifying air temperature or density in the environment of a nozzle toincrease flow through the nozzle, such as modifying air temperaturethrough heating air in the proximity of the outtake of the nozzle.

In embodiments, diffuser geometries may be a factor, such as exit angle,length of diffuser, splitting the diffuser in half, in quarters, and thelike, increasing the diffuser efficiency, the diffuser shape, the radialswirl, and the like. For instance, as the rate of constrictionincreases, the optimum diffuser may become longer, and longer as arelative ratio to the intake, such as at 2 there might be a 1:7 optimalratio of diffuser length to intake length, at 2.5 there might be a 1:9optimal ratio, and the like. The diffuser shape may be a curve, takenstraight to the outlet, convert the radial function to a polygonalfunction, use long or wide angle diffusers, use optimized nozzles forwind conditions with long diffusers, and the like. The radial swirl maycreate low-level swirl or higher rates of vorticity in the exit regionor rearward of the diffuser, where curved vaning may create an exterior,radial motion of the gas as it exits, which may create an additionallayer of sparsity inside the diffuser. In addition, the swirl may becreated using ambient air, vaning could be used with drill-through tointroduce the ambient air and increase the swirl, and the like. Othermechanical methods of creating sparsity as described herein may beutilized, such as an inverse rotor attached to the main KE convertingrotor may be used with an optimized geometry and an arrayimplementation. Such methods of increasing sparsity might allow the useof a non-optimized geometry that could have a positive effect on thecost parameters of the machine.

In embodiments, the relationship of intake geometry and diffusergeometries may change based on the rate of constriction. To create ahigh mass throughput, as you increase rate of constriction, the intakeand diffuser geometries may become far more important.

In embodiments, the rotor parameters may be important in the currentinvention, such as the shape of the blade and surfacing (which maycreate vortices both on the upper and lower surface of the blade). Aplurality of blade shapes may be employed, such as using vortexgeneration on the lower edge (which may add to the lift of the blade),lower angle for more power (but if the angle goes to zero, there may beno lift, so some low number may be good, such as a mean angle of fourdegrees), minimize the drag effect on the top of the blade due to theboundary layer effect (which may be hard to control if the direction thegas is coming from is unknown, so creating different kinds of bladeshapes that minimize boundary layer separation above the blade may bevaluable), drill throughs to address the boundary layer, making blades ainexpensively as possible, and the like. For example, the rotor may betwo meters long, formed of thermoplastic, could be hollow, and operatewith a basic swept-twist airfoil. Adjustable pitch may be used toincrease blade efficiency at higher velocities by adjusting to a lowerpitch angle.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air. A rotor maybe configured to operate within a wind power generating turbine wherethe rotor includes a complex topography vortex generation facility onthe blade, such as a vortex generation facility on the lower surface ofa blade, such as a vortex generation facility on the upper surface of ablade, vortex generation facility includes providing a dimple on thesurface of the blade, a shark scale topography, and the like. A rotormay be configured to operate within a wind power generating turbine,where the rotor may include a low angle relative to the plane ofrotation of the rotor, such as the angle being less than approximatelyfour degrees.

In embodiments, the rotor may be a variable inertia rotor, where if themass of the rotor is centralized around the hub, there is less inertiato start the rotor. In embodiments, there may be a facility forsmoothing the mechanical energy output of the rotor, the power capturemay be extended as the wind drops off where there may be more powerduring drop off as the weight is placed out on the edge, change thedynamics of rotor between low speed state and high speed state therebyholding it longer, and the like. In embodiments, the configuration mayshift the mass to the outward part as it gets as rotation rateincreases, such as by attaching a memory plastic spring, by using arubber elastic actuator, by using a metal spring, by spring loadedactuation, by actuation with a coil with a current going through it, bya fluid, by a mechanical actuator, by enlarging the rotor, throughcentripetal motion, and the like. By utilizing a spring, narrowing atlower speeds may be avoided, which may happen on drop-down of the wind.A start weight may also be used at the center, then move out and holdpeak power production with inertial at high speed and as the wind drops.In embodiments, a mass on a spring may be used to move the inertia outto the edge of the rotor, such as by putting a flat or round pipe up thecentral axis of the rotor, putting a mass on the spring, slotting it,and letting it get to the end, where as it slows down, the spring pullsit back in, or the spring releases a weight, and the like.

In embodiments, the rotor may utilize a variable blade, such as startingout with six blades, and then activate an actuator for pressure-basedswitch allowing some blades to collapse in order to reduce the totalnumber of active blades. For example, this may be done with any primemultiple, such as eight dropping to four and then dropping to two, ortwelve drops to six which drops to three, and so on. In this instance,the prime number blade may have the most structure, with the secondaryand tertiary with less structure, such as being made from thermoformsthat slot into the hub, and collapse as the wind speed increases. Inembodiments, energy capture at a given fluid velocity might go from 12%to 30% with the right blade number, so if one wants to get a good powercurve over a range, one might get the right blade configuration andmaximize over a whole range of velocities. This may translate into asignificant increase in annual yield. For instance, what is consideredlower speeds may be 60-70% of maximum (distribution) at any wind site.Today's systems often ignore the low wind, because one gets so much morepower out of the high wind areas. Most of East Coast on-land and closeurban sites (other than directly on shore—are class 3 or 4 sites. Theentire Southeast is a Class 1 site. Where the wind works now (Class 5),there are other problems, because of distance from major urban centers.Thus, setting up a system that works at low wind and still works at highwind is very effective.

In embodiments, the structural configuration of the module may beimportant to the present invention. For instance, the module may be anintegrated assembly that is put together separately with superstructureelements connected into the module, and then everything is connectedtogether. In embodiments, the structure could be a hexagonal, square,triangular, and the like arrangement that components are placed into, abasic geodesic structure and put module components into, and the like.There may be a need for actuators in the superstructure itself, so thatthe cover can be opened and closed. In embodiments one may build columns(power transfer columns) and fill in the space with modules. Eachsuperstructure element of a module may click into a bus that clicks intothe main one (as opposed to providing individual lines. If donemodularly, then one component could be popped out, and another poppedin, thereby providing a complete modular implementation, with a runningstock of replacement modules. In embodiments, the modules could be onsleds with their own way of getting down to the ground or may beinstalled by way of a built-in installation platform. There could alsobe a Pseudo-modular implementation, by making the super structure andinserting elements of the module individually. Components could beassembled in installation versus off-site. One could make modules inpieces, such as a clamshell top piece and a clamshell exit piece for thenozzle, where one puts the generator onto super structure first. Guidepoles or a form of guided crane may be utilized for removal of parts forreplacement. There may be a slot in the superstructure, such as forwardand rearward on the superstructure with slotting poles such that modulesare installed onto the slotting poles. Modules may be manufacturedon-site, such as manufacturing in a tractor-trailer, where for instance,nozzles may be made on site. Once the process is automated, thelikelihood of human error may be lower.

In embodiments, there may be wildlife protection/anti-fouling systemssuch as screens on the same pole as used on the superstructure, wherebirds and bats may pose a problem. In embodiments, bugs may not be asignificant issue, but there may be self-cleaning surfaces utilized,such as certain plants, like lotus leaves, where viscosity of theinherent molecules may not bond to the surface. Modularity may allowslotting out the screens and cleaning them. In embodiments, the presentinvention may provide a nozzle or array of nozzles adapted for use in awind power generating turbine, where the nozzle may be adapted forextreme conditions, such as earthquakes, high wind, ice, and the like.The adaption for extreme conditions may include mechanisms to allow thenozzle to survive earthquakes, where the mechanism may be a fluidfoundation, a gyroscopic mechanism, a pintle mechanism, a frequencydamping mechanism, and the like. The adaption for extreme conditions mayinclude mechanisms to allow survival of high winds, such as category 5winds. The adaption for extreme conditions may include mechanisms toallow for partial structural degradation of the nozzle. In addition, theadaption for extreme conditions may include mechanisms for deicing thenozzle. The nozzle may also be protected by a wildlife inhibitor, suchas a broadcasted sonic inhibitor, a mechanical screen, an olfactoryinhibitor, and the like.

In embodiments, arrays of nozzles and the arrangement of the arrays maybe an important aspect of the invention, where there may be advantagesin an arrayed configuration. For instance, as compared to monolithic, ifan efficient proportion is one to ten, then you may need much more powerto efficiently use the space required by a monolithic nozzle, and it maynot be stable without some structural components made out of expensiveaerodynamic materials. In certain embodiments, the distance needed toreestablish flow after the outlet of the turbine is approximately thedepth of about one array, and one may thus stack arrays behind eachother, such as in the checkerboard of FIG. 2 or in a co-mountedconfiguration.

In embodiments modules may be configured in the arrays to cover asignificant portion of the plane of the array. In embodiments the bestway to cover the plane may be to have the truncated catenoid geometry.If a comparison is made between an array and a conventional turbine, onemay start to see big differences, such as an array on platform comparedto a tall turbine. Additionally, the area of the array may not have tobe a fixed shape or size. For instance, the array could start at 30 mand go up to 90 m, or it can start lower. In embodiments, the presentinvention may provide an array of nozzles adapted to generate electricalpower from the flow of air, where the array may include nozzles ofvariable type at different height. For instance, some nozzles may belarger at greater heights than nozzles at lower heights, have lowerconstriction at greater heights than nozzles at lower heights, and thelike. The array doesn't have to have a circular structure, so it mightbe 115 m by 35 m, or alternately, it might cover a similar swept area ina similar of different proportion. In embodiments, more power may bederived, because there is more area at the higher wind speed. Anotheradvantage may be that in a traditional single large blade turbine theremay be different wind speeds at the top verses the bottom of the prop,and the difference may produce uneven stress loads and production atsome mean figure. In the current invention each row may get more thanthe rows at the bottom, with no stress load between the top and bottomrows. The top one or two rows, on their own, may gather more than theentire traditional turbine prop. The ability to manipulate how youhandle the area of the array is a major factor in generated power,footprint, and the absence of the need for custom building, and thecurrent invention may allow the custom design, generating energy basedon the power curve, wind distribution, and the like. In embodiments,with an array design, the configuration for an efficient, modular, spaceframe super structure may be re-used for many different sites.

In embodiments, array parameters may include the optimal number ofmodules, where the parameters may include tangential wind loads, icing,inertial components, cost of making the rotor, load bearing, poweryield, area covered, nozzle depth, tradeoff of height and depth, and thelike; the vertical starting point at which the array begins; thevertical point at which the array ends; the width of the array; depth ofthe array; shape of the modules, such as square, diamond, hexagon,triangle, rectangle, combined packing shapes of polygons, packingpolygons, and the like; shape of the array, such as square, diamond,triangular, trapezoid, shaped cladding (where something that bleeds thewind in the direction the nozzles bleeds the wind, with duplicateoutside coverage of the nozzles, and/or extending of the cladding);variability of the modules, such as sizes and shapes; bearings, such asbetween array rows to orient independently or for the whole array, amagnetic bearing, a wind bearing, bearings for rows of arrays, and thelike; uniformity, such as outside modules smaller than inner modules orthe inverse, impact on structural bearing of the array, impact on theelectrical distribution, and the like; load bearing properties, such asmanaging load across the array; the ability for a series configuration,such as placed end-to-end, in a grid, based on a fraction of the exitspeed, and the like; turbulent mixing over the outer part of the module,such as with vortex generators, axial stream tubes, like drill-throughs,trailing edge on airfoil with vortex generator, optimizing the trailingair mix; combined outer shape of the array; the superstructure;installation properties of the individual array; installation propertiesof the wind farm, such as dimensions relative to each other;arrangements of the arrays; and the like. In embodiments, laying out thearrays into a wind farm configuration may entail a plurality of designparameters, such as the minimum optimal dimensions across the array, thefront array numbers and dimensions verses the back, where the arrays areplaced in the wind farm, whether the wind farm can be placed near urbanspaces, on top of a hot spot, close to transmission line, and the like.

In embodiments, the super structure parameters may present importantaspects to the present invention, such as modularity; applying spaceframes to the superstructure of the array; integrating with the shape ofa given module; integrating with the power structure; load bearingsupports, such as relative to the length of the modules, a need forlateral support, square shapes bearing less than a diamond shape, andthe like; shaped space frame, such as cladding on the space frame,deciding which members need to be thick, placement of lateral support,and the like; structural space frame as an electrical conduit;transferring power through the super structure, such asattaching/conducting power, placement of busses, placement ofconnectors, need for main bus columns, attachment of modules within thestructure to the main bus column, running wire from each one to acentral bus to transfer to the grid in one big cable, minimizingresistance to help allow efficient distribution of energy, minimizingcomplexity and cost of installation and maintenance, and the like; pipeshapes; superstructure weight distribution; and the like. Inembodiments, the present invention may provide a structural array forgenerating electrical power from the flow of air, wherein the structuralarray may be a composite space frame wind producing array superstructure. The space frame may be made of composite or alloy materials.The space frame may include variable profile structural members,variable solidity members, variable members, fixed members, and thelike. The space frame may also include properties to enhance structuralproperties, material use, material cost, material weight, and the like.

In embodiments, the electrical system may present important aspects tothe present invention, such as electrical distribution within thesuperstructure; dynamic voltage regulation; high voltage handling; loadregulation; load management/load parsing, such as a higher load on theupper end of the array, parsing the load on a single machine with anarray of turbines, and the like; load splitting; power/energy transfer,such as power conditioning of power from any array, network architectureto distribute load, managing a network, neural networks, substation,grid interface, and the like. In embodiments, the storage system maypresent important aspects to the present invention, such as whetherenergy to compress a fluid or gas, where energy diverts from the gridinto a compression system to say, run turbine compressors off of energy,a water vessel to use heat as you are compressing, blowing compressedair into vortex tube, radiators on bottom of circulating chamber, builda mini version of the wind in a circulation chamber, put turbines in theconfiguration to produce a very efficient storage system, making windflow based on hot and dense using nozzles to convert that helpsstabilize the output over an hour and then goes out to the grid,stabilize over an hour, use vortex tubes to create massive pressuredifferentials, and the like.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where anelectrical load management facility may be provided for managingvariable electrical load associated with different power generationcomponents of the array. Alternately, a mechanical load managementfacility may be provided for managing variable electrical loadassociated with different power generation components of the array.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may include power control. The power control may be networked ornon-networked. The networked power control may include power transfer,such as power transfer being integrated into the structural components,external to the structural components, including a network topographythat minimizes resistance losses utilizing at least one of a branch andtrunk network structure and direct generator-main trunk connectionstructure, and the like. The networked power control may optimize thepower production within the array and monitor power production of thearray for performance, maintenance, replacement, and the like. Thenetworked power control may dynamically manage load requirements for atleast one of a plurality of arrays. The networked power control may useoptimization methods such as neural networks, genetic algorithms, fuzzyalgorithms, probabilistic predictive-corrective feedback loops and thelike, to provide maximizing output, minimizing losses, and the like. Thenetworked power control may use a dedicated communications system, arouting system, distributed communications system, and the like, tocontrol individual network elements within at least one of a pluralityof arrays. The networked power control may utilize digital control,analog control, and the like, may utilize an electronics, electronicschip, electronics logic, and the like, use centralized or distributedprocessing, be hard-wired or wireless, including at least one of anelectronics chip and management algorithm, and the like.

In embodiments, the present invention may provide an array of nozzlesadapted to generate electrical power from the flow of air, where thearray may include power conversion elements, power management elements,and the like. The power conversion and management elements may beconnected to a power frequency converting mechanism, power conditioningmechanism, and the like, to prepare the power generated for storage,transmission, use, and the like, where the mechanism may be an LVDCconverter, HVAC converter, LVDC frequency converter, HVAC frequencyconverter, and the like. In embodiments, power management may be local,global, and the like. The power conversion and power management elementsmay utilize power diodes, thyristors, transistors, power MOSFETs, IGBTs,and the like. In embodiments, the power conversion and power managementelements may operate the array for fixed speed generation, operate thearray for variable speed generation, performed by electrical facilities,performed by mechanical facilities, and the like.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may convertkinetic energy from the wind into at least one of electrical andmechanical energy. In embodiments, the conversion may be made with aconversion mechanism including at least one of a DC direct driverotating machine, AC direct drive rotating machine, flywheel, generator,transmission/gearbox, synchronous singly-fed DC rotating machine,synchronous singly-fed AC rotating machine, asynchronous singly-fed DCmachine, asynchronous singly-fed AC machine, asynchronous doubly-fed DCmachine, asynchronous doubly-fed AC machine, induction singly-fed DCmachine, induction singly-fed AC machine, induction doubly-fed DCmachine, induction doubly-fed AC machine, MHD DC rotating machine, MHDAC rotating machine, Maglev DC rotating machine, Maglev AC rotatingmachine, low-speed DC rotating machine, low-speed AC rotating machine,medium speed DC rotating machine, medium speed AC rotating machine, highspeed DC rotating machine, high speed AC rotating machine, variablespeed DC rotating machine, variable speed AC rotating machine, fixedspeed DC rotating machine, fixed speed AC rotating machine, variablefrequency DC rotating machine, variable frequency AC rotating machine,fixed frequency DC rotating machine, fixed frequency AC rotatingmachine, squirrel cage DC rotating machine, squirrel cage AC rotatingmachine, permanent magnet DC rotating machine, permanent magnet ACrotating machine, self-excited DC rotating machine, self-excited ACrotating machine, superconductor DC or AC rotating machine,superconductor AC rotating machine, 1-n phase DC rotating machine, 1-nphase AC rotating machine, coreless DC rotating machine, coreless ACrotating machine, vibrational mechanism, and potential energy basedmechanisms. The conversion mechanism may also be controlled by at leastone of an electrical and mechanical power control management facility.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includespeed and load management facilities wherein the speed managementoptimizes the relationship of rotor speed, power conversion, andaerodynamic losses. The speed facilities may include electrical ormechanical mechanisms to operate the machine at variable or fixed speed.The load management facilities may include either electrical ormechanical management of the load applied to the rotor or generator.Electronic load management may be performed by means of powerelectronics. Mechanical load management may be performed by means of atransmission or gearbox or a geared, CVT, or applied field type.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine, where the nozzle may includepower conversion management elements. The power conversion managementelements may be connected to at least one of a power frequencyconverting mechanism, power frequency conditioning mechanism, LVDC toHVAC converter, LVDC to HVAC frequency converter, and the like, toprepare the power generated for at least one of storage, transmission,and use. The power management may be local, global, and the like. Thepower management elements may utilize power electronics, such as a powerdiode, thyristor, transistor, power MOSFET, IGBT, and the like. Thepower management elements may operate the array for fixed speedgeneration, variable speed generation, and the like. In embodiments,power management may be performed by mechanical facilities.

In embodiments, detailed aspects of the nozzle configuration may beimportant to the present invention, where the differentiators betweencurrent technologies and the current invention may include polygonaltruncation of a figure of revolution to create the underlying geometry,leading edge (LE) geometry as constrained/determined by intake length,curvature, and LE angle relative to constriction, use of intake andconstriction parameters to determine diffuser geometry, and the like.

In embodiments, the current invention may use a particular nozzlegeometry to accelerate a flow under constriction to a high percentage ofits theoretical velocity increase. The nozzle may conform to the basicConverging-Diverging or DeLavel structure with the constriction rate ofthe convergent end serving to accelerate the incoming flow and thediverging to “re-expand” said flow. The nozzle geometry may be based ona molecular fluid dynamics theory that differs substantially from thecontinuum approach and is also dissimilar to numerical methods, such asLattice Boltzmann Method (LBM's) or Monte Carlo methods. The nozzlegeometry differentiators may include the basis geometry, specificgeometry with regard to LE characteristics and volumetric ratios, andsurface geometry.

In embodiments, plane use optimization may be achieved by way of a basisquadric surface geometry wherein the inlet and exit geometry of thenozzle is formed by an asymmetric (with regard to both axes) hyperboloidof revolution of one sheet truncated at an orthogonal regular orReuleaux polygonal boundary. The hyperboloid of revolution may beobtained by the use of an asymmetric catenary function or a closelysimilar combination of radial/elliptical or truncated radial/ellipticaland linear functions. In an adjusted catenary form the hyperboloid ofrevolution can be obtained with the following equations and conditions.For the intake mapping values the hyperbolic cosine function,y=a*cosh(x/a), can be used for the set of real numbers where x<0 andwhere ‘a’ is determined as a function of desired rate of constrictionand intake length. For exit values, the set of real numbers where x>0,the following formula is used, y=(a^(n)*cosh(x/a^(n)))−(a^(n)−a), wheren determines the rate of divergence/increase from the initial (0, a)throat value for the y values of the function.

In embodiments, the polygonal truncation of the hyperboloid ofrevolution may allow the nozzle to cover a polygonal intake area withvariable intake curvature while having an effective momentum focusingcircular structure and expanding to a closely similar polygonal outletarea. The ability to cover a non-circular, for example a square inletarea, may immediately yield more efficient use of the fluid plane. Thepreferred polygons or combinations thereof are those that can be tightlypacked and provide a minimal surface area solution with regularpolygon/s used for complete plane coverage or Reuleaux polygon/s usedwhen a percentage of freestream flow through the given structure isdesired. Higher order regular polygons may also be used to allow apercentage of freestream flow.

With regard to the exit it can be formed either by truncation of theasymmetric catenoid or linear element or by interpolating the relativearc curvatures to from a value of 1/r_(t) at the throat (where r_(t) isthe radius of the throat) to 0 at the exit expanding therein to thedimensions of the entrance polygonal truncation. In the case of theReuleaux polygon the curvature of the arc segment forming the sides isused as the lower value. In the regular polygon and Reuleaux polygonexit cases the geometry is based on the figure of revolution but doesnot constitute a figure of revolution. Additionally, in the case where aportion of parallel exit is preferred this can be added as an extensionof the truncating polygon. In this regard, global (e.g. for the wholenozzles vs. a bounded area in the nozzle) rate of constriction andthereby the parameters of a regular truncating polygon is given by,

$\begin{matrix}{{{r = {{Ai}/{At}}},{or}}{r = {{\frac{\left( {n/4} \right)s^{2}{\cot \left( {\pi/n} \right)}}{{\pi \left( {{.5}d_{t}} \right)}^{2}}\mspace{14mu} {or}\mspace{14mu} s} = \frac{r\; {\pi \left( {{.5}d_{t}} \right)}^{2}}{\left( {n/4} \right)\mspace{14mu} \cot \mspace{14mu} \left( {\pi/n} \right)}}}} & {.5}\end{matrix}$

where n is # of sides, s is the side length, r is the rate ofconstriction, and d_(t) is the desired throat diameter.

The resultant geometry may be constrained by the following parameters inorder to insure high-mass flow through the nozzle. The initial angularLE value of the radial or catenary function for the curvature of theconstrictive region can be determined two dimensionally in its simplestform by using a radial arc approach and is given by the convergence of ifor the following equations,

$i = \frac{{.5}\left( {d_{I} - d_{t}} \right)}{{{1/\sin}\; \theta} - \left( {{{1/\sin}\; \theta^{2}} - 1} \right)^{.5}}$and$i = \frac{d_{t} - {{.5}\left( {d_{I} - d_{t}} \right)}}{\tan \; \theta}$

-   wherein:-   θ=vector resulting from initial incident leading edge angle-   i=intake length from leading edge to throat-   d_(I)=diameter of intake-   d_(t)=diameter of throat    Dependent on the value of y and the rate of constriction, this can    be a catenary, radial, elliptical, or truncated radial, truncated    elliptical, or combination thereof constrictive/convergent section.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. A nozzle may be adapted for usein a wind power generating turbine, where the maximal optimal curvatureof the nozzle intake may be determined two dimensionally in its simplestform, such as in the case of a radial arc, may be given by theconvergence at the initial angular leading edge, such as the value of ifor the following equations: i=(0.5(d_(I)−d_(t)))/(1/sinθ−(1/sinθ²−1)*⁵) and i=(d_(t)−0.5(d_(I)−d_(t)))/(tanθ), where θ=vector resulting frominitial incident leading edge angle, i=intake length from leading edgeto throat, d_(I)=diameter of intake, and d_(t)=diameter of throat. Thisoptimization may be applied two dimensionally or three dimensionally toa catenary, radial, elliptical, truncated radial, truncated elliptical,or the like function. In addition, a nozzle may be adapted for use in awind power generating turbine, where the optimal curvature of the nozzleintake may be greater than two times the throat diameter.

The geometry of the i value convergence may be applied globally acrossthe intake derived from an i boundary maxima or at some lower boundary ivalue. It may also be applied locally with interpolated values, whereinthe truncation boundary's minima and maxima are solved separately andthen used with a weighted interpolation (matching the curvature of themaxima-minima interstitials) to determine the local i convergencerelative to varying intake lengths across the polygonal boundary. Whenapplied locally the resultant geometry does not conform to a normalfigure of revolution as in the divergent case above. An additionalconstraint herein is that the mean value for i be preferably equal to orless than the diameter of the nozzle throat. An additional constraint isto maximize the rate of curvature of the wall within the other geometricparameters and this can be inherently optimized by the precedingequations. In this regard the value of θ can be relaxed by a coefficientdefined by the following relationship: C_(r)=1+2((1/r)^(r)), wherein ris the rate of constriction. Thereby the relaxation coefficientapproaches a minimal value as the rate of constriction increases.

Extant “optimal” intake curvatures, researched under pressurizedconditions, indicate that the optimal curvature for a radial nozzle,regardless of rate of constriction, is an arc section from a circlebetween 1.8 to 2 d where d is the diameter of the throat. Research infurtherance of this invention has shown that such curvature engendersthe loss of a large portion of the mass available at the intake area.

With regard to the divergent portion of the nozzle an angular value fromthroat to exit may be used to determine the volumetric ratio of thedivergent length to convergent length. The constraint herein is that theangle of the divergent wall be no more than 5 degrees, with the anglerelative to rate of constriction preferred being described by thefollowing equation, Ø=C_(d) (a+b+b^(5+a)) where a=1/r^(r), b=r^(1/r),and C_(d) is an adjustment coefficient related to intake length, whereinr is the rate of constriction. Therefore the divergent geometry in thecurrent invention is predicated on a ratio of rate of constriction tointake length to divergent length that results in convergent todivergent volumes wherein the volumetric ratio increases with the rateof constriction. It is this combination of specific LE geometry with avariable, rate of constriction and intake dependent,convergent-divergent volumetric ratio that enables high percentage massflows. Additionally the complexity of the surface geometry of the nozzlecan be increased by application of quadric or other complex structuresto the basis geometry. This may include small-scale structures used forflow enhancement or larger scale structures for structural or flowenhancement.

Said quadric functions can be bounded to create n-structure surfaces,e.g. scales or dimples, or can be applied globally across the surface asin corrugation or scalloping or rearward truncated scalloping, boundedby the initial truncating polygon. Scale and origin points of thequadric structures can be varied and the surfaces can be compound, withmultiple layers of quadric structures mapped against the precedinglayers' basis geometry. This allows the combination of various globaland local flow-enhancing elements to maximize the nozzle massthroughput. Additionally said quadric structures can have drill-throughsin either single layer or channel implementations to the near wallcharacteristics of the flow.

In embodiments, the present invention may provide a nozzle adapted foruse in a wind power generating turbine. The nozzle may include avariable wall profile, such as a wall profile utilizing linearscalloping. The nozzle may include complex wall topography, where thecomplex wall topography may maximize structural properties, minimizematerial use, minimize material weight, and the like. The complex walltopography may have a uniform circular profile, polygonal profile, andthe like. The complex wall topography may provide a variable profile,such as with linear scalloping, being generally radially curved, beinggenerally elliptically curved, and the like. The complex wall topographymay provide a variable density structure, uniform, variable, and thelike. In embodiments, the complex wall topography may provide nozzlecomponents that may be variably adapted to the lowest cost solution forlocal load bearing parameters within the nozzle. The complex walltopography may provide nozzle components that are made of rigidmaterials, flexible materials, and the like.

In embodiments, the performance characteristics may be provided. Anumber of single layer quadric truncated and non-truncated nozzles havebeen fabricated based on the above parameters. Nozzle constriction rateshave ranged from 2-4 with regard to the ratio of the intake to thethroat. In cases where the desired rate of constriction exceeds 4,single layer quadric geometries are insoluble as i tends to infinitywithin the constraint of the LE vector solution. In such casesmulti-layer and/or multi-body quadric structures are preferred. Nozzleswere fabricated in two throat size ranges 25 cm and 10 cm with theattendant geometric parameters deriving from the structural descriptionsabove.

As is well known in the art the Bernoulli equation describes thecontinuum pressure-velocity relationship of a fluid flowing through aconstriction wherein the rate of constriction results in an equal rateof acceleration for the mass in question as detailed by the change in KE(u) and internal energy (p). The majority of extant work in nozzleoptimization is therefore based on pressure measurements. There ishowever a substantial divergence in the prior art (Reid et al) betweenthe empirical measurement of volumetric mass flow and pressureefficiency of nozzles. This indicates that, with regard nozzleefficiency, pressure might not be the most accurate variable. The massthroughput of a particular nozzle geometry is the variable of primaryimportance in categorizing efficiency. Mass flow efficiencycategorization of these nozzles derives from velocity and power data. Incomparing velocity results with power results, which are directlydependent on mass throughput, the nozzle performance can be accuratelyjudged by their close agreement. The velocity relationship relies on themass flow equation, Mdot=puA, where p equals density, such that, forgiven areas A₁ and A₂, Mdot_(a1)=p_(I) A₁ u_(I), and Mdot_(a2)=p_(t) A₂u_(t), and solving for u_(t) with Mdot and p values being the same forboth in incompressible flow gives, u_(t)=u_(I) A₁/A₂ or simply the u_(I)value is multiplied by constriction ratio of the intake to the throatthereby providing the theoretical velocity increase in u for a givenconstriction.

Mass loss to the exterior of the nozzle will therefore be apparent inthe velocity measurements based on the following, where the maximum massflow rate is Mdot_(max)=p u_(I) A₁ and, Mdot_(actual)=pu_(a)A₂, massloss % at throat=u_(a)A₂/u_(I) A₁=Mdot_(actual)/Mdot_(max) by which themass efficiency of the nozzle can be judged based on actual velocitymeasurements. With regard to power analysis, the power equation can bederived by combining the KE and mass flow equations wherein the Mdotterm is substituted for the mass term. Thereby the theoretical ratio ofpower at the intake and throat adjusted for area difference becomes,

$\begin{matrix}{R_{{pt}:{pi}} = \frac{\left( {A_{i}\left( {A_{t}/A_{i}} \right)} \right)*p*\left( {u_{i}{A_{i}/A_{t}}} \right)^{3}}{A_{i}{pu}_{i}^{3}}} \\{= {\frac{A_{t}}{A_{I}}*\frac{\overset{3}{u_{i}A_{I}}}{A_{t}}*\frac{\overset{3}{1}}{u_{I}}}} \\{= \frac{\overset{2}{A_{I}}}{A_{t}}}\end{matrix}$

And therefore,

Pt=Pi*R _(pt:pi)

And the nozzle mass flow can be expressed as a function of power,Mdot_(actual)=P_(actual)/0.5u_(actual) ² Where, u_(actual)=(0.5A_(t)p/P_(actual))^(1/3) and given simultaneous measurement inside andoutside the nozzle, Mdot_(actual)/Mdot_(max)=(P_(actual)/0.5u_(actual)²)/(P_(max)/0.5u_(max) ²). Where, u_(max)=u_(I)A_(i)/A_(t)=(0.5A_(t)p/P_(max))^(1/3) and, P_(max)=P_(i)*(A_(i)/A_(t))². Thus the samemass loss rate can be determined as in the velocity case. For example anozzle with a constriction of 2 would yield a 2 times velocity increaseand a 4 times power increase. If the mean measured velocity increase is1.7, the mass flow efficiency would be approximately 0.85 of the maximalvalue. With regard to power this mass flow results in a power increaseof approximately 2.5. Conversely, a mean velocity increase of 1.85indicates a 0.94 value for mass flow which results in a 3.3 powermultiple.

With regard to the structural parameters described above optimum massflow performance range for this nozzle type is detailed in the followingtable:

Table of Optimum Parameters for Structural Variables with MassThroughput and Measurement Ranges:

Mdot V inc. P inc. r θ _(LE) C_(r) L_(i)/d_(t) L_(d)/L_(i) Ø _(D) % meanmean 2   31 0.5  >1, >6  <2   .92-1 1.8-2 3-4 opt .5 2.75 270.12 >1, >8  <1.5 .95-1 2.5- 5.625- opt .8 2.75 7.56 4   25 0.03 >1, >12<1   .815- 3.25- 8.66- opt ~ 1 0.9 3.6 11.6

It was found that divergent length and function thereof is mainlydependent on intake length not throat diameter, as in prior art,although in higher rate constrictions these values are forced toapproach each other by geometric and curvature constraints. Variation ofthe intake length and the diffuser length but not the throat diameterresulted in little or no performance difference, providing the ratio ofL_(d)/L_(i) was maintained, L_(i)<d_(t), and the nozzle conformed to theother geometric parameters. Variation of throat diameter with staticL_(d)/L_(i) proportions again resulted in little or no performancedifference.

The optimum divergence angle was found to differ from those previouslydescribed in the art. It was also found that the narrowness of theoptimum range was inversely proportional to the rate of constriction.Mass throughput degraded steeply in testing outside the optimum rangedescribed. Higher rate constriction nozzles were especially sensitive.Additionally it was found that variation of intake length in excess ofthe described range substantially degraded performance especially ifcombined with a variation of the diffuser length below the describedrange.

No substantial mass flow difference was noted between truncated andnon-truncated nozzles of the same rating, indicating that the truncatednozzle might be more efficient simply based on its geometric coverage ofthe wind plane, and therefore preferred. Additionally a 2.75 nozzle hada secondary quadric layer applied after its initial phase of testing. Aperformance improvement based on power capture was noted. Additionallythe nozzles were tested in staged and nested configurations wherein inthe first case the nozzles were tested at some nominal separation withlittle or no performance degradation. In the second case nozzles werenested within each other with the smaller being placed at a nominaldistance rearward of the larger throat to achieve better throughput onhigher rate constrictions.

As detailed in the previous section nozzle flow acceleration is premisedon the principle of conservation of mass. Bernoulli and Navier-Stokesequations are considered the governing equations for fluid flow atstandard pressure and density. This regimen is generally known as thecontinuum regimen wherein a fluid model is based on macroscopicproperties. Navier-Stokes equations are usually solved numerically as nogeneral solution is known. In addition to these approaches there arevarious numerical methods applied to fluid flows ranging from LatticeBoltzmann to Monte Carlo methods. At some level however most of thesesolutions are based on empirical adjustment of the theoretical result tomatch test data. Additionally there is very little wide-scopeexperimental data regarding the performance of nozzles. Gibson and Reidprovide the most comprehensive data in the art but in both cases thestudies are limited to isolating the effects of one characteristic ofthe nozzle such as 2 dimensional divergent length in Reid. Most recentwork is premised on numerical estimations or design testing.

Numerical studies such as Tekriwal use pressure variables to calculateaccuracy of numerical simulation against empirical pressure data, butignore flow rates or derive flow rates from the pressure variables.Additionally the basic assumptions therein are based mainly on the workof Gibson and Reid which are relatively constrained in scope.Problematically prior art provides no satisfying explanation for thenozzle's improved function with the divergent section in the subsonicregimen. Likewise there is little research on the actual properties of aflow along a gradient. Formulas such as the linear interpolationpressure gradient force (PGF) equation,

${{F\left( {m/s^{2}} \right)} = {\frac{1}{p}*\frac{p_{1} - p_{2}}{n}}},$

approximate flows reasonably well but do little explain the mechanismsof the flow itself or the properties said flow displays either atinitial condition or in steady state. As can also be seen thesimultaneous use of the pressure and density terms is problematic.

This can be said generally of the fluid dynamics equations. They arevery good for approximating performance under specific conditions,usually pressurized, but generally the solutions do not matchexperimental data closely in the area under consideration, e.g. mismatchbetween theoretical performance and test data that is especially true ofnozzles. The almost complete lack of research in non-pressurizedconditions adds to the imperfect understanding of nozzle function. Thedivergence between experimental data and theory is usually explained byvariation of a real gas from an ideal gas or frictional effects or someslight error in fabrication. More likely it is due to oppositionalgeometry enhancing flow effects that would otherwise by masked by thefree volume proportions of single-body research.

Since single-body constitutes the majority of solid body research dataand the basis of Prandtl boundary layer theory and Blasius' work, theerror rate in predicting nozzle performance is a strong indicator thatthere are some inherent flaws to understanding the mechanics of flows asembodied by the fluid dynamics (FD) equations. For these reasons extanttheory does not provide a solid basis from which to optimize nozzledesign in and of itself. Given the dearth of experimental data in thearea especially in the subsonic regimen this means that use of extanttheory to enhance design is mainly educated guesswork.

Since an efficient nozzle design is one of the purposes of thisinvention, it was desirable to develop a flow model which indicateddifferent design paths by which a nozzle might be optimized, one whichexplained the interaction of the various nozzle regions and whichmatched experimental data. This requires a detailing of the problemswith the current set of assumptions and development of a model of thetypes of flows a nozzle such as the designs described herein are likelyto encounter in operation and thence a more in depth description ofsolid body interaction with said flows.

The most pressing problems in this regard may include, assumption ofsolid body interaction being substantially similar regardless of thetype of fluid flow, use of the Pressure Gradient “force” (PGF) toexplain the mechanism of fluid flows, assumption that subsonic flow inthe continuum regimen is of uniform density, assumptions associated withthe distinctness of free-stream and boundary layer, assumption thatpressure can provide a substantially accurate description of fluidbehavior, assumption that pressure, velocity, and density aresubstantially differentiated variables, and the like.

First there are two distinct conditions that result in fluid flows. Oneis when a displacement volume is introduced into a fluid system thatresults in the distribution of the momentum from the volume ofintroduction throughout the system until the system again reaches astate of equilibrium. Two is when energy is introduced into a fluidsystem that effects the system-wide distribution such that flow iscreated by the properties of the imbalance in distribution and continuesuntil a state of equilibrium is again reached. Solid body interactionwith a flow that is substantially of one type or another must, by itsvery nature, have different parameters. Any given flow is likely toinclude elements of each type of flow (e.g. a plane flying into aheadwind), but the majority of interaction in a given localized systemcan usually be ascribed to one or the other. These two types of flow arebest described as wake flow and gradient flow. In the first caseintroduced force drives the flow, whereas in the second case densitydrives the flow.

This brings us to a second adjustment with regard to the current modelof flows. Both the macroscopic and microscopic properties of a fluidflow are describable by revising the variable set used. In this regardthe Bernoulli equation can be characterized as a statement of proportionand, while useful for measurement, it is not very useful for mechanics.The macroscopic pressure-velocity relationship is simply a convenientdescription of the proportion of unidirectional net momentum vs.omni-directional momentum at the molecular level as determined by thethermal/energy properties of the system in question, wherein theunidirectional component is the bulk velocity and the omni-directionalis the bulk “pressure”. In the case where this net flux across thesystem in question has not been caused by displacement, there is onlyone potential source - statistical movement based on the kinetic energyof the molecules in the system and a variation in molecular density.

This can be most conveniently viewed in the context of an n-dimensionalmatrix for which the population of the matrix has n degrees of freedomfrom state t to state t+1 wherein the probability of any given path issubstantially equal and random and the population is constrained toshift position at every time step, e.g. Brownian motion. The desiredsampling rate of said matrix would be the mean molecular separationalthough the matrix can be scaled to represent the mean properties ofgroups of molecules. If the matrix is subjected to a sparse-densemapping wherein the population of the matrix is denser in area a than inarea b, then the statistical net momentum/movement, e.g. flow, is foundin the dense to sparse direction. Providing an approximation of thermalenergy input into a system by constraining density variation at eachtime step to be substantially similar to the preceding time step, thismethod of representation provides a close approximation of short-termsteady state flow as one might find in a wind system.

From this model it is clear that gradient flows are a statisticalexpression of the density variation in a system and the level of kineticenergy present in the system, not the product of PG “force”. Thereby thecontinuum assumption of uniform density in a fluid flow in the subsonicregimen is clearly at odds with the mechanics of the flow itself.Therefore the assumption of uniform density must be held to localconstraints of intermolecular repulsion and thermal expansion.

Additionally it can be seen that both the macroscopic properties ofvelocity and pressure are functions of the microscopic properties ofmolecular density, root-mean-square (RMS) velocity, and translationalmomentum. In this regard these macroscopic variables can be done awaywith in favor of the more accurate model. This revised model must now bedeveloped to be of use in solid body design. The first step therein is adefinition of the mechanics of the flow.

Similar to the rest energy calculation the potential maximum of the flowin terms of energy or velocity can be calculated based on aninstantaneous unidirectional flow, e.g. all molecules flowing from astandard density region to vacuum, by setting the velocity equal to themean RMS velocity of the mass under examination. In this way anyportional flow can be characterized as a percentage of the RMSunidirectional velocity.

Since velocity can be expressed as a function of momentum and mass, thevelocity of a given intermolecular slice can be expressed as the nettransfer of momentum and mass between slices with the mass transferbetween the slices determined by the density : sparsity difference. In asteady state flow this transfer would be constant between the slicessomewhat similar to a cascade effect.

In this regard there will be a net momentum increase between any givenpair of slices, n_(n) and n_(n+1). At each slice n₁, n₂, n₃ . . . n_(n)the momentum increase will be additive in the sparse direction as eachslice has a net momentum increase between samples t and t+1. Thereby thevelocity profile of the gradient field is dependent on the specificdense sparse distribution of molecules for the field in question and thesum of momentum transfer and number of slices within the field.

In this way the macroscopic properties of velocity, e.g. the bulktransfer of mass over a given distance, can now be represented by themicroscopic fluid conditions and more specifically the microscopicmomentum field.

This is of special import with regard to the introduction of a solidbody into the gradient field. Specifically with regard to nozzles thisimplies that the velocity increase at the throat is no longer a functionof mass conservation as in the continuum model. Instead it results fromchanges in the density gradient field caused by the introduction of thesolid body and differences in the momentum transfer resulting from thosechanges.

The nature of the field in the steady state may be such that the maximalvalue the rate of momentum transfer may be concurrent with the maximalrate of change in the density gradient wherein said rate of change canbe assumed to be non-linear and likely parabolic.

With the uniform density constraint relaxed and the bulk properties nolonger dependent on mass conservation, this has substantial implicationswith regard to boundary layer. Assumptions of the distinct separationbetween conditions in the boundary layer and the freestream are nolonger valid as the foundation for the boundary and freestreamseparation is the mass continuity of the freestream.

It is useful now to treat the nozzle as a separate field within thelarger density field. Assuming steady state condition for a nozzle in agradient flow, the maximum rate of constriction for a radial inletnozzle occurs at the leading edge of the nozzle inlet. This implies thatthe greatest density change within the nozzle field will occur in theregion of the leading edge. Density will increase proportionally to thelocal rate of constriction and the thermal constraints of the field andthereby momentum will increase in the flow direction at a similar rate.

This has several implications for the visible boundary layer. While somemomentum is lost in the LE region as incident molecules collide with thenozzle wall, subsequent collisions should conform to general parametersof elastic collisions between molecules. Thereby there exists a mean(e.g. statistically directional diffuse reflection) direction of the nmolecules incident to the LE, with some parameter of momentum loss. Themomentum vector of the molecules deflecting from the LE region willreflect into the stream upon each collision while the individualmolecules will continue to collide with incoming molecules on a meanfree path basis until the initial incident path becomes closelyorthogonal to the nozzle wall. Under this model there is a formation ofa boundary layer which satisfies the no slip and visible boundary layerconditions but this boundary layer does not contain the momentum as isassumed in extant boundary layer theory.

With regard to design optimization this implies that the LE vector is ofsubstantial importance in transferring momentum into the inward intakeregions. Additionally this implies that there is a relationship betweenthe rate of constriction and parameters of the LE dependent nozzlefunction as is borne out by experimental data.

Conversely there is a limit at which the density increase becomes suchthat the net momentum transfer from the external field into the LEregion is opposed by the density increase such that there is alsoprobabilistic momentum transfer in the direction generally opposite tothe flow engendering mass loss. Such a condition leads to theentrainment of less mass into the nozzle and mass and momentum loss tothe exterior of the intake and a lesser rate of momentum transfer to theinward regions of the intake.

This condition can be experimentally observed most easily in aconverging nozzle. In a converging nozzle as the rate of constrictiongrows the rate of velocity increase is noted to shrink indicating a massbuild up in and forward of the intake. This is observable in smokevisualizations of converging nozzles wherein when the rate ofconstriction becomes sufficiently large the flow becomes stagnant to thepoint where the observable boundary layer does not form. Length overwhich the constriction occurs also contributes to this effect. It canalso been seen in the attachment of shock to a solid body in the sonicregimen.

A velocity increase is noted in the use of a converging nozzle usuallyat much lower rate than the theoretical increase. An examination of thedensity gradient in the converging section is of interest here. As theLE density condition increases a region of additional sparsity iscreated rearward of the LE. In the case of a strictly converging nozzlethe exterior field density at the throat is not a sufficient gradientfor the flow to attain a rate of momentum sufficient to clear the LEdensity and allow the full mass available at the intake to enter thenozzle.

Under such conditions it is likely for the momentum field to beparabolic achieving a maximum rate within the inlet where the rate ofconstriction acts as a counterbalance to the potential maximum rate oftransfer.

As a note this model also serves to explain the experimental differencebetween radial and straight inlets. In a radial inlet the maximum rateof constriction is localized to a relatively small region wherein thedensity increase is localized. Conversely a straight or funnel inlet hasa constant rate of constriction creating a constant density increasethrough the intake to the throat.

With a localized density region at the LE the diffuser functions toincrease the dense sparse rate of the gradient field which the nozzlecontains. The increased diffuser length with increased constrictionserves to increase the volumetric ratio by which the gradient iscontrolled and thereby clear the forward density in the LE region. Basedon the rate of constriction and thereby the rate of LE density increase,the length of the diffuser determines whether the rate of maximummomentum transfer is at or close to the throat.

If this maximal rate is clear of the intake region, a condition existssuch that the increased density is cleared and the limiting conditionresulting in flow opposing the flow field is not reached. The increasedvelocity at the throat is thereby due to the combination of the gradientbetween the LE region and the exit and the initial momentum influx fromthe exterior field. In this regard the diffuser serves to control boththe properties of the gradient field and the rate at which the mass andmomentum transfer occurs from the throat to the exit.

In embodiments, this describes the basic function of the nozzle regionsunder a revised model. This model delineates the properties of thedifferent nozzle regions and provides a foundation both for theexplanation of regional function and the design of high throughputnozzles. In illustration of the above discussion, FIG. 27 depicts anozzle with truncation intake and exit 2700, FIG. 28 depicts a Nozzlewith truncated intake and 1/r-0 interpolated curvature 2800, and FIG. 29depicts an arc section diagram for inlet geometry 2900.

In embodiments, aspects of a variable blade rotor are presented. Avariable blade number-type rotor is described wherein the number ofblades a rotor presents to the flow varies with flow speed. In anembodiment, FIG. 30 depicts a six-blade open configuration 3002, showingthe primary 3004 and secondary 3008 blade, and the primary 3010 andsecondary 3012 hub of the pressure mechanism. As is well known in disctheory, rotors with different numbers of blades and different profileshave performance profiles that closely fit a given flow velocity range.Since it is desirable to optimize the power output of a flow drivenpower device, a rotor that adapts the disc solidity presented to theflow would be more efficient at gathering power across a variety ofspeed regimens than a fixed solidity rotor.

A 3-blade rotor efficiency plot 3100 is shown in FIG. 31. C_(p)represents the proportion of power available at the area covered thatthe rotor is able to convert. This is a direct result of the rotationalspeed as it relates to tip/blade speed and the loading of the rotorthrough the generator. The power plot of this relationship forms thewell-known power curve.

FIG. 32 shows a Weilbull distribution of annual velocity 3200. Taken incombination these result in FIG. 33, a comparison 3300 of a 6>3-bladeC_(p) profile and a 3-blade C_(p) profile for annual power:velocitydistribution. As linear velocity increases, tip speed increases, and therotor reaches a limiting rotational value based on the aerodynamicproperties of the blades and disc solidity making the typical 6-bladedrotor inefficient in the ranges above 6 m/s.

While this efficiency range is highly dependent on the loading schemeboth with regard to the gearbox/transmission and electrical loads,assuming an optimized design for both mechanical and electrical loadingthere is a clear efficiency limit to a blade set based on its rotationalspeed. Enhanced loading schemes, as plotted 3400 in FIG. 34, that shiftthe rotational aerodynamic efficiency range upward without negativelyeffecting efficiency of power capture are preferred in this invention.That said, in the 1 m/s to 6 m/s range the 6-bladed rotor captures moreof the KE available in the raw flow. Given a situation wherein themajority of a given flow on a time period basis is in the lower rangesthe advantage of having variable disc solidity is clear.

The variable solidity rotor may have a plurality of prime number rotorssets (e.g., 1, 2, 3, 5, etc) co-axially mounted inclusive of a facilitywhich allows the secondary, tertiary, . . . nth rotor set to slot intoeach preceding set. As an example, for a 3 blade primary rotor withthree sets, the initial stage would be a 12 blade rotor which wouldclose to a 6 blade rotor and then into the primary set of 3.

The facility for closing said primary rotor sets may be inclusive ofboth dynamic pressure driven and/or actuator/mechanical methods. Rotorsets can either be of closely similar properties in terms ofaerodynamics and mass or of divergent blade structural, mass, andaerodynamic properties.

In embodiments, rotor sets may be mounted to a series of dual positionslip rings wherein when the dynamic force on a given set is exceeded thering is released and dynamic force on the blades shifts it to a closedposition on the following set of blades. A mechanism is slotted onclosure such that when the dynamic force on the closed blade setsindicates a drop in velocity the blade set is released to open position.

In this embodiment the rotor is constituted of 3 sets wherein theprimary set is a structurally reinforced swept-twist thin airfoil bladeand the secondary set and tertiary sets are thin swept-twist airfoils.The camber geometry of the secondary set is fitted to the lower surfaceof the tertiary set and similar fitting geometry is used for the primaryand secondary sets. Geometry is such that the blade pitch between statesis not altered. Each set is optimized for higher-speed profiles, toextend the usable range of each blade state to maximum efficiency.

In embodiments, the primary blade set is inclusive of structuralcomponents that allow mass distribution to be controlled on the rotorper provisional application. FIGS. 35-38 show certain aspects of theblade configurations previously discussed, where FIG. 35 depicts 12blades in an open position 3500, where velocity is approximately in therange of 1-3 m/s, FIG. 36 depicts 6 blades in an open position 3600,where velocity is approximately in the range of 3-6 m/s, FIG. 37 depicts3 blades in a closed position 3700, where velocity is approximately 6+m/s, and FIG. 38 depicts a sample of open and closed profiles 3210,where the open profile shows the primary blade 3802, the secondary blade3204, and the tertiary blade 3208.

In embodiments, an inertial rotor may provide advantages by enhancingrotational stability under dynamically variable conditions, wherein theoutward centripetal force of the rotation is used to enhance the inertiaof a rotating body by way of a variable radius mass distribution system.A material may be allowed to move based on centripetal motion toward theouter radius of the rotating body. This can be executed with anymaterial that can be controlled in its balance under centripetal force.Said material can also be controlled by way of actuators.

In embodiments, an inertial rotor may be comprised of single orplurality of rigid or semi-rigid bodies symmetrically or asymmetricallyjoined in a contiguous or non-contiguous manner around a centroid ofrotation wherein there exist facilities to control the mass distributionwithin the plane/planes of rotation and thereby the inertialcharacteristics of said rotation in a manner advantageous to the desireduse.

In embodiments, the invention may constitute a rotatable body 302, asshown in FIG. 39, with a central mass reservoir 3904, a facility forcontrolling said mass 3908, and an outer mass reservoir 3904. Saidreservoir can be either a single or plurality thereof. The initialcondition is with the mass central to the axis of rotation wherein thereis little additional energy required to begin rotation. As the body'srotation accelerates the mass may be moved toward the outer radius 3910and 3912 through the mass control mechanism 3908, which may include butnot limited to centripetal acceleration or mechanical or otheractuators. The additional mass in rotation on the outer portion of thebody provides a more stable rotation with greater relative inertia.

In embodiments, the control of the mass within the rotor radius may beachieved by way of variable mass flexible structures, e.g.weights/springs or memory plastic/foam or other suitable material knownin the art, wherein the flexible structure, with an external element ofthe structure having greater mass than the internal element, iscontained in an housed chamber extending axially through a single orplurality of solid bodies. As rotation and centripetal force increasethe weight will extend the flexible structure to the maximal desiredexternal radius of the rotating body. As detailed below these structurescan include magnetic properties of use in both mass distribution controland field generation.

In embodiments, a contiguous substance is housed within a single orplurality of central portion/s of the rotor assembly wherein channelsextend axially through a single or plurality of bodies attached to saidcentral hub. The substance can be any substance that conforms to a givenviscosity wherein the substance will shift mass toward the outwardradius through the channels only under rotation while maintainingcontiguity through the radial channels and central hub such that ascentripetal force is reduced the viscosity (coherence) of the substancewill draw the outer mass back into the central hub. As detailed belowsaid material can also include magnetic properties of use in both massdistribution control and field generation.

In embodiments, a fluid may be allowed to cycle through a single orplurality of axial channels. Said fluid can be a standard dense fluid orcan be fluids with special properties such as magneto-rheological fluidswherein the electro-magnetic properties of the fluids can be used tocontrol mass distribution within the solid body under rotation. In sucha rotating body the magnetic fluid, or other magnetically “enhanced”substances or structures such as those mentioned above, while beingcontrollable in its distribution through the body by way ofelectromagnetic fields may also serve the purpose of generating usefulelectro-magnetic fields as the substance or structure achieves itsmaximal radial position. Such executions of the current invention can beachieved with either a fixed method of field generation or incombination with a single or plurality or counter-rotating bodies. Inaddition, mechanical actuators may be used to granularly control themass distribution of the substance or structure under consideration.

FIGS. 28-31 show embodiments relating to aspects of an inertial rotor asdescribed herein, where FIG. 40 depicts a weighted structure initialposition 4000, FIG. 41 depicts a weighted structure in a subsequentposition 4100, FIG. 42 depicts a 3 blade structure in motion 4200, andFIG. 43 depicts a 3 blade structure 4300 with mass control channel 4302and central mass reservoir 4304.

While the invention has been described in connection with certainpreferred embodiments, other embodiments would be understood by one ofordinary skill in the art and are encompassed herein.

All documents referenced herein are hereby incorporated by reference.

What is claimed is:
 1. A system comprising: a plurality of wind energyconversion modules interconnected into a scalable modular networkedsuperstructure adapted to convert wind energy into electrical power froma flow of air, wherein each one of the plurality of wind energyconversion modules includes a nozzle, the intake of the nozzle having afirst opening and a second opening that is parallel to the first openingand that is smaller than the first opening, the intake of the nozzlehaving a generally catenoidal shape, the shape having an axisperpendicular to the openings and being truncated by a plane along theaxis, the plane being perpendicular to the axis.
 2. The system of claim1, wherein the catenoidal shape is a hyperboloid of revolution obtainedby the use of an asymmetric catenary function.
 3. The system of claim 1,further comprising an outtake diffuser having a first opening and asecond opening that is parallel to the first opening and that is largerthan the first opening and the first opening equal in size to the intakeof the nozzle second opening, the outtake diffuser having a generallycatenoidal shape, the shape having an axis perpendicular to the openingsand being truncated by a plane along the axis, the plane beingperpendicular to the axis.
 4. The system of claim 3, wherein thecatenoidal shape of the intake of the nozzle is continuous with thecatenoidal shape of the outtake diffuser.
 5. The system of claim 1,further comprising each one of the plurality of wind energy conversionmodules with a rotor positioned to receive the flow of air from theintake nozzle and a generator coupled to the rotor.
 6. The system ofclaim 5, wherein the converting to electrical power is by way ofconverting the flow of air to mechanical energy in the rotor of each oneof the plurality of wind energy conversion modules and converting therotational energy to an electrical energy in the generator of each oneof the wind energy conversion modules.
 7. The system of claim 1, whereinthe scalable modular networked superstructure is rotated to orient thescalable modular networked superstructure toward the air flow.
 8. Thesystem of claim 1, wherein the air flow is captured and accelerated withthe module intake nozzle of each one of the plurality of wind energyconversion modules.
 9. The system of claim 1, wherein the plurality ofwind energy conversion modules includes nozzles of variable size. 10.The system of claim 1, wherein the nozzles of the plurality of windenergy conversion modules include a plurality of self-orienting nozzleswith independent orientation at different locations in the scalablemodular networked superstructure.
 11. The system of claim 1, wherein atleast one of the wind energy conversion modules contained in thescalable modular networked superstructure includes a plurality ofnozzles configured in series relative to a direction of the flow of air.12. The system of claim 1, wherein the scalable modular networkedsuperstructure has a variable width at different heights.
 13. The systemof claim 1, further comprising optimizing management of a power outputfrom the plurality of wind energy conversion modules with a loadmanagement facility.
 14. The system of claim 1, wherein the rotor of atleast one of the plurality of wind energy conversion modules isconfigured to have varying amounts of inertia.
 15. The system of claim1, wherein the rotor of at least one of the plurality of wind energyconversion modules is configured to present a variable number of blades.16. The system of claim 1, further comprising storing the electricalenergy for at least one of later use, contributing to a regulation ofenergy output of the scalable modular networked superstructure, andallowing the scalable modular networked superstructure to function as abase load grid unit.
 17. The system of claim 1, further comprisingmodifying an air temperature in an environment of the nozzle of at leastone of the plurality of wind energy conversion modules to increase flowthrough the nozzle.
 18. The system of claim 1, wherein the scalablemodular networked superstructure is a composite space frame windproducing array superstructure.
 19. The system of claim 1, wherein thescalable modular networked superstructure is integrated with an arrayelectrical distribution system.
 20. The system of claim 1, wherein thescalable modular networked superstructure uses complex variable walltopographies to provide at least one of maximized load bearingproperties, minimized material use, and minimized material weight.
 21. Awind power generating turbine comprising: a rotor assembly within thethroat of a nozzle, wherein the throat of the nozzle is in fluidcommunication with the wind power generating turbine; and a supportingsuperstructure for the turbine that includes materials enabling alighter than air implementation.